AMERICAN SOCIETY FOR TESTING MATERIALS

1916 RACE STREET

PHILADELPHIA 3. PA.

1951
REFERETILTS
on.
r /I I lla Lib
STPNo. 9-1 YV'%
This is a list of references to articles published in 1957s*4fc&to&,with
fatigue of structures and materials, following the plan used in previous^ann^
lists from 1950 through 1956. References are generally so arranged that sheets'
can be cut apart for filing according to any desired plan. Brief abstracts have
been included when these were readily available.
Comments and suggestions concerning the value and format of this list
would be appreciated. Correspondence should be addressed to
Dr. Horace J. Grover, Chairman
Survey Subcommittee III
ASTM Committee E-9
Battelle Memorial Institute
505 King Ave., Columbus 1, Ohio
Sponsored by ASTM Committee E-9 on Fatigue
$3.00
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 STP9I-EB/Jan. 1957
ANDERSON, S.P. ANONYMOUS
International Institute of Welding, Annual Aircraft Fatigue Handbook, Volume II -
Report of Commission XVI: Welding Instruc- Design and Analysis. (ARTC/W-76 Aircraft
tion o Structural Fatigue Panel).
BRITISH WELDING JOURNAL (ENGLAND) 4, No. $ AIRCRAFT INDUSTRIES ASSOCIATION, INC.
p. 236, May 1957. January 1957.

ANDERSON,, W, J. ANONYMOUS
Performance of 11C mni bore M-l tool steel Bending-Fatigue Tester for Sheet Materials.
ball bearings at high speeds, loads and
temperatures. THE ENGINEERS1 DIGEST (ENGLAND) 18, No.8
p.372, August 1957.
NACA TECHNICAL NOTE TW3892 ( Jan. 1957).

ANONYMOUS ANONYMOUS
Accelerated Fatigue Testing of Aircraft
Components Can Ultrasonics Speed Fatigue Testing?
ENGINEERING (BRITISH), VOL 183, pp 247 MSTALWORKBJG PRODUCTION, VOL. 101
(Feb. 22, Iy5f?) p. 1032 (June 14, 1957).
Four machines capable of completing Description of new Mullard high speed
•within 12 months the entire component- fatigue machine.
fatigue-testing program for a major air-
^craft project, are being installed by

ANONYMOUS ANONYMOUS
Short Brothers and Harland, Limited, Defects and Failures of MetaJ^^he^
Belfast. Hydraulically operated machines Origin and Elimination. pocjj^jSfc
are being installed that are capable of lished by Cleaver-Hume Press-Xtdo
applying loads of 100 tons, ten times per (England).
second. Avery-Schenek machines are being
installed that are capable of imposing loads Reviewed in THE ENGINEER (EnglftW
up tp 20 tons on small joined specimens. 203, No. 5274, pp. 301 and 304
February 22, 1957.

Copyright© 1957 by ASTM International www.astm.org

ANONYMOUS ANONYMOUS
Effect of the Shape of Test Bars on the Fretting Fatigue
Fatigue Resistance of Peraluman 50 Alloy
(Inflenza della forma delle provette sulla METAL INDUSTRY, (ENGLAND) 90, No. 21,
resistenza a fatica della Peraluman 50). pp. 444 and 446, May 1957*
ALLUMINIO (ITALY) 26, No. 6, pp.251-254
June 1957.

ANONYMOUS ANONYMOUS
Fatigue Failure of a Metal-Sprayed Crank- Fatigue Research by the European Economic
shaft. Cooperation Organization
(RECHERCHES SUR LA FATIGUE PAR 1'O.E.C.E.)
SHIPBUILDING AND SHIPPING RECORD (ENGLAND) REV. ALUMINUM (ERANCE) 34, No. 247, p.938,
89, No. 25, pp 808-809, June 20, 1957 October 1957.
The European Economic Cooperation Organiza-
tion has worked out an international pro-
gramme for systematic research on fatigue.
The experimental work will be carried out
in Belgium, Canada, France, Germany, Great

Cont!d Fatigue Research by the European,etc,

ANONYMOUS
Britain, Italy, the Netherlands and Sweden.
Fatigue Failures Twenty-five pulsators, operating with ten-
sion-compression stresses, and thirty-five
SE7. SOITK (FRANCE) 13, No. 1, pp.60-66, rotative-flexure machines will take part in
1957, and BIBLIOGRAPHICAL BULLETIN FOR the tests for which some 8 tons of light
WELDING (FRANCE) 9, No. 7/9, page 252JE, metals will be allotted. A group of spec-
July-September 1957. imens will be subjected to a predetermined
fatigue treatment followed by testing at
various stress levels.
Ultimate purpose of the study is to deter-

ANONYMOUS Cont'd Fatigue Research by the European, etc,

Fatigue Fractures and How to Avoid Them.
(English) mine the shape and position of the resid-
ual Wohler curve, and, hence, to assess
ACIERS FINS & SPECIAUX FRANCAIS, 1957 the damage sustained by the metal during
No. 27, December, pp.48-57. the initial fatigue treatment.
Fatigue fractures are often due to imper-
fections in the form of pieces both on
the geometric and microgeometric scale.

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ANONYMOUS ANONYMOUS

Fatigue Strength Data for Cast Steels Fatigue Testing

and Cast Iron (Japanese).
THE AEROPLANE (ENGLAND) 42, No. 2375
JAPAN SOCIETY OF MECHANICAL ENGINEERS page 340, March 8, 1957.
JOURNAL, VOL. 60, May 1957-
Tables and graphs of fatigue limit and
tensile strength, stress-strain cycles
and related experimental data.

ANONYMOUS
ANONYMOUS
Fatigue Strength Data for Copper and
Copper Alloys (Japanese). Fatigue Testing

JAPAN SOCIETY OF MECHANICAL ENGINEERS METAL INDUSTRY (ENGLAND) 91, No. 1

JOURNAL, VOL.60, May 1957. page 11, July 1957.

Tables and graphs of the creep, tensile

strength and stress-strain cycles of
copper and copper alloys; data for plate,
bar and cast copper alloys.

ANONYMOUS
ANONYMOUS
Fatigue Strength Data on Structural
Alloy Steel (Japanese)
JAPAN SOCIETY OF MECHANICAL ENGINEERS, Fatigue Testing Equipment for Aircraft
JOURNAL, VOL. 60, May 1957. Components.
Structural alloy steel data tabulated as THE ENGINEERS* DIGEST (ENGLAND) 18,
follows: fatigue limit and tensile strength; No. 4, PP. 169-170, April 1957.
stress-strain cycles. Included are nickel-
chromium steel, nickel-molybdenum steel,
chromium steel, aluminum-chromium-molyb-
denum steel, stainless steel, spring steel.

ANONYMOUS ANONYMOUS
Fatigue Strength of Light Alloys (Japanese) Fatigue Testing Machine for Spring Wire.
JAPAN SOCIETY OF MECHANICAL ENGINEERS
JOURNAL, VOL. 60, May 1957. NATIONAL BUREAU OF STANDARDS TECHNICAL
NEWS BULLETIN 41, 63, April 1957.
Tables and graphs of the creep, tensile
strength and stress cycles for aluminum Description of a machine for applying
and aluminum alloys, magnesium and mag- cyclic torsion to small diameter wire.
nesium alloys.

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ANONYMOUS ANONYMOUS

Fatigue Tests on Mild Steel Plate. Large Scale Fatigue Tests on Complete
Sections of Aluminum and Magnesium Alloys
Typewritten document, 8 pages, and MINISTRY OF SUPPLY (GREAT BRITAIN) 1957
BIBLIOGRAPHICAL BULLETIN FOR WELDING
(FRANCE) 9, No, 4/6. page 94E, April- It has been shown on three aluminum alloys
June 1957. and one magnesium-base alloy tests that
conventional methods of fatigue testing
using small machined and polished cylin-
drical specimens or coupons can give re-
sults which in no way indicate that fat-
igue strength of the unmachined sections

ANONYMOUS Confd Large Scale Fatigue Tests, etc.

Hard Anodic Finishes. from which the specimens were cut. The
testing teachniques employed, that is,
LIGHT METAIS, pp 156-157 (May 1957). rotating cantilever and reversed bending,
do not in themselves appear to have con-
tributed markedly to the observed dif-
Includes statements that hard anodizing ferences in fatigue strength, but there
reduces fatigue strength of strong alloys is evidence to support the view that a
25 - 30#, but this can be improved by rectangular-shaped section gives a slight-
subsequent boiling in dichromate. ly lower fatigue strength than a round
specimen.

ANONYMOUS ANONYMOUS
Hard Finishing Processes Compared. Lectures on Fatigue
LIGHT METALS, pp. 167-169 (May 1957)
SHEET METAL INDUSTRY (ENGLAND) 34
Compares (a) hard anodizing, (b) hard No. 368, page 928, November 1957.
plating and (c) spraying. Includes
discussion of effects on various mech-
anical properties, including fatigue
strength.

ANONYMOUS ANONYMOUS
Internal Tests on Metal Fatigue Mechanical Properties and Fatigue Re-
sistance of Submerged Arc Welded Joints
SHEET METAL INDUSTRY (ENGLAND) 34
No. 364, page 625, August 1957. PRZEGL,SPAW,(POLAND) 9, No. 3,
pp. 84-88, March 1957, and
BIBLIOGRAPHICAL BULLETIN FOR WELDING
(FRANCE) 9, No. 7/9. page 247E
July-September 1957-

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ANONYMOUS ANONYMOUS
Motion Pictures of Metal Fatigue Reports on Fatigue Failures
ASIM BULLETIN No. 220, p. 20 (Feb. 1957)
SHEET METAL INDUSTRY (ENGLAND) 34,
A small fatigue testing machine., designed No. 361, page 375, May 1957.
at the National Bureau Standards for test-
ing specimens under alternating torsion,
is described. The machine is of the con-
stant-strain type, the load being deter-
mined by the degree of eccentricity of two
cams.

Cont'd Motion Pictures of Metal Fatigue ANONYMOUS

It is equipped with a 16 mm motion picture
camera attached to a metallurgical micro- Research Into Fatigue Fractures
scope for studying the surface changes oc-
curring during fatigue. FOUNDRY TRADE JOURNAL (ENGLAND) 103,
No. 2135, page 312, September 1957.
Preliminary tests on aluminum showed the
normal development of slip bands, their
intensification, crack initiation, and
the sudden extrusion of very thin ribbon.

ANONJMOUS ANONYMOUS
Now Titanium is Cheaper; Its Properties
and Uses. Safety in Mines Research Establishment
Article on production, uses, and properties Laboratory.
of Titanium. Staall section on fatigue pro- THE ENGINEER (ENGLAND 203, No. 5285,
perties in general by Dr. N.P.Inglis, Res.
Director, I.C.I.Metals Div. page 731, May 10, 1957.
ENGINEERING (BRITISH), VOL. 183, The equipment of the Safety in Mines
pp.298 (March 8, 1957) Research Establishment includes a 20-
ton pulsator used for fatigue tests on
General Comments: chain links, and a 400-ton machine for
(l) Fatigue strength of titanium and titan- testing pit arches. This equipment is
ium alloys was high. described and illustrated.
g Contf d Now Titanium is Cheaper:
ANONYMOUS
(2) Under completely reversed loading the
ratio of endurance strength to tensile dbiength The Effect of Wetting Agents on the Cor-
for commercially pure Ti. is 0.5, while for rosion Properties of Aluminum-7^ Mag-
alloys the ratio rose to 0.6. Titanium and nesium Alloys, With Special Regard to
Ti alloys ratio of endurance strength to Corrosion Fatigue.
tensile strength is closer to steel than to (Einfluss von Netzmitteln auf die Kor-
aluminum alloys. The high rate of fatigue rosion von A3Mg7 unter der sonderer
strength to tensile strength is the same at Berucksichtigung der Ermudungskorrosion)
elevated temperatures as it is at room tem-
perature . Z. METALLKUNDE (GEHMANY) 48, No. 5
(3) Fatigue notch studies are not complete but pp. 232-240, May 1957.
for the work completed. However, the broad
conclusions to date are that titanium is not
unduly peculiar as regards notch sensitivity
effects.
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ANOJJYMOUS ANONYMOUS
The Fatigue of Metals These Curves Give Fatigue Properties
of Reinforced Plastics.
(Series of lectures published in book
form by the Institution of Metallurgists, MATERIALS IN DESIGN ENGINEERING, Vol.46
28 Victoria St., London, SW. 1, 1956. July 1957, pp* 108-111.
148 pages,)
Data on glass-reinforced laminates
Supplement of TRANSACTIONS OF THE INST. subjected to repeated stresses,,
OF MARINE ENGINEERS (ENGLAND) 69, No. 3,
pages iii, March 1957.

ANONYMOUS ANONYMOUS

The Influence of Building Up by Electric Warm Drawing Improves Fatigue Life

Arc Welding on the Fatigue Strength of
Medium Carbon Steel Shafts. STEEL, VOL. 140, No» k, pp. 94-95
(Jan. 28, 1957).
Typewritten document, 11 pages, and
BIBLIOGRAPHICAL BULLETIN FOR WELDING SAE 1340 type steel, drawn from 600F-
(FRANCE) 9* No. 4/6, page 94E, 1200F| Rcajc30; no heat treatment.
April-June 1957o

ANONYMOUS ARBLASTER, H.E,

The Sulfinuz Treatment of S.80 and S.99
Steels,, Effect on Fatigue Strength and Effects of Chromium Plating on the
Other Properties. Properties of High Strength Steel
MINISTRY OF SUPPLY (GKEAT BRITAIN) July 1957- JOURNAL AUSTRALIAN INST» OF METALS,
Tensile, Izod impact, fatigue and corrosion VOL. 2, pp.54-71 (April 1957).
tests have been carried out on two steels
treated by the "SULFINUZ11 process. A signif-
icant improvement in fatigue strength is A surveys effect of plating conditions
noted when compared with steels treated in and of heating to remove hydrogen.
a neutral salt bath. Under severe corrosion
conditions the "SULFINUZ11 treated specimens

Cont'd The Sulfinuz Treatment BARROIS, W.

The Evolution of Fatigue in Metals
show greater attack with marked local action, (Evolution des metaux en fatigue)
A preliminary metallographic examination
is described. REV. ALUMINUM (FRANCE) 34, No. 246
page 790, September 1957

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BALDWIN, -E.E., C. J. SOKOL, AND L* F. BARNETT W.Jo AND A.R. TROIANO
COFFIN, JR. Crack Propagation in the Hydrogen-In-
Cyclic Strain Fatigue Studies on AISI duced Brittle Fracture of Steel.
Type 347 Stainless Steel
JOURNAL INST. OF METALS, VOL. 9, also
AS1M PREPRINT No. 64, 1957 ANNUAL MEETING. TRANSACTIONS AIME, VOL.209, pp.486-494
(April 1957).
Constant temperature, cyclic strain tests
were carried out on type 347 stainless The mechanic sm of static fatigue fracture
steel in a special axial loading machine. was investigated using SAE-A151 4330
The strains varied from 0.0035 to 0.02 in./in, steel heat treated to various strength
and the temperature from room to 600°C levels with hydrogen introduced by
(cyclic frequency not stated). Effects cathodic charging.

;Cont'd Cyclic Strain Fatigue Studies

Cont'd Crack Propagation in the..etc.
*of grain size^anisotro'py and sequence
of loading were studied. The specimens were placed under static
The results were i» good agreement with stress and crack growth and propagation
the relationship N*^^&f« c, where N is were studied by heat tinting metallo-
the number of cycles, ^v£p the plastic graphic sectioning and electrical re-
strain, and fc! a constant related to the sistance measurements.
fracture ductility (about ^). Neither
grain size nor aaisotropy appeared to have
a significant effect on this relationship,
but temperature had a marked effect on
-'c1 which was not revealed by the fracture
ductility.

Cont'd Cyclic Strain Fatigue Studies BASTENAIRE, F.

A Critical Study of the Notion of Damage
Applied to an Extensive Class of Fatigue
From a modification of Miner's relation- Tests.
ship, the life under sequential loading
varied from 72 to ±63% of the life in PROCEEDINGS COLLOQUIUM ON FATIGUE,
single-level tests. STOCKHOIM, SWEDEN, in May 1955, Pages 1-13,
1956. METAL ABSTRACTS (ENGLAND) 24,
Part 8, page 615, April 1957.
Bastenaire makes a statistical study of
the fatigue behaviour to be expected when
the stress amplitude is varied. The con-
ception of damage is introduced as an

BASTENAIRE, F., R. CAZAUD, AND M. WEISZ,

;Contfd A Critical Study of the..etc.
Statiscal Fatigue Tests by the Method
of the Progressive Charge. additive function, so that at each
moment during a fatigue test the state
PROC. COLLOQUIUM ON FATIGUE, STOCKHOIM of the sample can be characterized by
(SWEDEN) in May 1955, PP 14-23, dis- one parameter, and equivalent treatments
cussion 23, 1956. followed by any identical treatments give
final equivalent results.
The results of fatigue tests on a steel
sample are examined statistically.
METAL. ABSTRACTS (ENGLAND) 24, Part 8
-7-
page 659, April 1957.
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BEAR, Ho, ROBERT AND ROBERT H. BUTLER BELSHEIM, Ro 0.
Preliminary Metallographic Studies of Ball Delayed-Yield Time Effects in Mild Steel
Fatigue Under Rolling-Contact Conditions. Under Oscillatory Axial Loads
NACA TN 3925 NATIONAL ADVISORY COMMITTEE ASME TRANSACTION, p. 1619 (October 1957).
FOR AERONAUTICS. MARCH 1957 38 pages,
diagramss photos. An apparatus was developed which loads a
tension specimen by a vibratory load super-
The metallurgical results produced on balls imposed on a static load. Tests of mild
tested in rolling-contact fatigue spin rig steel produced (a) dynamic yield points
were studied by metallographic examination. 5 to 50 per cent above the static yield
Origin and progression of fatigue fail-
ures were observed. These evaluations were
sCont*d Preliminary Metallographic, etc. Cont'd Delayed-Yield Time Effects, etc,
. made on SAE 52100 and AISI M-l balls fatigue
tested at room temperature (80° F) and 200° point, and (b) corresponding delayed-
to 250° Fo Most failures originated sub- yield times of 1000 to 10 millisec.
surface in shear, inclusions, structure These results showed general agreement
changes, and directionalism adversely af- with the results of other investigations.
fected ball fatigue life. Structures in
the maximum-shear-stress region of the balls Report contains graphs, schematic diagram
of both materials were stable at room tem- of testing apparatus, tabular data, and
perature and unstable at 200° to 250° F0 photographs of vibratory-test records.
Failures were of the same type as those
^ found in full-scale bearings.
Copies obtainable from NACA, Washington

8 Cont'd Preliminary Metallographic, etc. BERRY, Wo Ro

1. Surfaces, Contact-Rolling (3. 8. 3)
20 Steels (5-1- 3) Spring Design.
3. Materials, Properties-Fatigue (5. 2. 5)
4. Materials <, Operating Stresses MECHANICAL WORLD AND ENGINEERING RECORD
and Conditions (5. 3) V. 137, pp. 398-401, SEPTMBER 1957 and
5. Research Equipment, Materials (9. 1. 6) V. 137, pp. 466-470, OCTOBER 1957-
The improvement of spring life by shot
I. Bear, H. Robert peening and methods of providing for it
II.Butler, Robert H. in design.
III. NACA TN 3925

BENNETT, GUY V. BIDHELL, J 0 B.

Recrystallized Surfaces of Aluminum Fatigue Durability of Carburized Steel.
Extrusions,
AMERICAN SOCIETY FOR METALS, CLEVELAND
METAL PROGRESS, VOL« 72, page 102, 123 pages, 1957 (TA473 AM 35f)
December 1957.
The influence of processing upon the met-
Specimens from large-grained material near allurgical properties, residual stress
surface had much lower static and fatigue distribution, and fatigue properties of
properties than interior. carburized steel are evaluated experi-
mentally.
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BIJXING,, B.Fo and BINNING, M.S. BOLLENRATH, FRANZ
The Tensile and Fatigue Properties of Torsional Fatigue Strength of Some Heat
nimonic 80A (Extruded) and Nimonic 95 Treated Alloy Steels with an Induction
at Elevated Temperatures. Hardened Case.
ROYAL AIRCRAFT ESTABLISHMENT (GREAT ARCHIV FflR DAS EISENH§TTENWESEN, VOL. 28,
BRITAIN), July 1957. No* 12, pp 801-806 (DECMBER 1957)
The tensile and fatigue properties are given Unnotched 20Han dia cylindrical specimens
for extruded Nimonic 80A at 750°, 8150 and made of four different alloy steels were
875° C and for Nimonic 95 at 850°, 875° and tested in reversed torsion. The specimens
900 C, the latter material in two conditions were heat treated to about 110 kg/mm2
of heat treatment. The fatigue ultimate tensile strength, and then in-
duction hardened. The case depth varied

Cont'd The Tensile and Fatigue, etc. Gont>d Torsional Fatigue Strength, etc.
between 0.16 mm and 3«5 nm. S-N curves are
tests were performed in Haigh type direct plotted for different steels and different
stress machines at both zero and various case depths. Metallographic investigations
tensile values of mean load. were done and hardness readings taken.
At small case depths the torsional fatigue
strength is lower than that of plain heat-
treated specimens. With increasing case
depths the fatigue strength increases con-
siderably | and at case thicknesses lar
than 1.2 to 202 mm the fatigue strength of

BLOCMER* No T. s Cont'd Torsional Fatigue Strength, etc.

Time-saving in Statistical Fatigue induction-hardened specimens is larger
Experiments. than that of plain heat-treated specimens.
ENGINEERING (BRITISH) It is assumed that this behavior is caused
by residual stresses from induction hard-
p. 603 (November 8, 1957). ening.
2 tables, 13 figures, 11 references«

BOKROS, JoC. BORIK, F., R. Do CHAHCAN, AND WoE. JCKINY

Effect of Sodium on the Mechanical Effect of Percent Tempered Martensite on
Properties of Zirconium. Endurance Limit.
AMERICAN SOCIETY FOR METALS, TRANSACTIONS
NORTH AMERICAN AVIATION, INC. (U.S. ATCMIC VOL. 50, PREPRINT NO, 16, 1957.
ENERGY COMMISSION) NAA-SR-1867, 39 pages,
June 1957. (UF?6? Un3.Ina Contin.) The endurance limit drops with the presence
of small percentages of nonmartensitic pro-
Surface oxide which develops on Zr in Na ducts. As the percent of martensite de-
significantly lowers the fatigue life at creases below 85 percent, the endurance
elevated temperatures, but has little ef- limit is not as sensitive to microstructure,
fect on tensile properties. Data also
indicate that Zr is stable to dimensional
changes after thermal cycling. -9-
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BOLUS, 'KENNETH H. BREEN, J. E, AND JOSEPH Re LANE'
Fatigue Properties of Fibrous Glass-Rein*, Effect of Dispersion of Alpha Phase on the
forced Plastics Laminates Subjected to High Temperature Fatigue Propertiep of
Various Conditions. Alpha-Beta Brass.
MODERN PLASTICS, V. 34, P< 163 + 11 pages
JUNE 1957. TRANSACTIONS, AMERICAN SOCIETY FOR METALS,
VOL.XLIX, pp 959-977, 1957.
Fatigue strength values are presented for
six standard and four heat-resistant resin By varying the heat treatment of 60$ Cu,
laminates reinforced with glass fibers. 1^ Sn, 39# Zn brass, the authors produced
material having varying amounts of dis-
persed alpha phase in a matrix of beta
brass„ Creep and axial tensile fatigue

sCont'd Fatigue Properties of Fibrous, etc *Cont'd Effect of Dispersion of Alpha, etc,

Fifty-three S-N curves, representing fatigue tests on specimens machined from these mat-
data between one thousand and ten million erials were made at temperatures of 500,
cycles, show the effect on fatigue strength 600 and 700 F0 Tensile fatigue and stress-
of notching, moisture, fabrics, resins, rupture tests were not affected in the same
mean stress levels, angles to warp, and way by temperature and dispersion changes.
temperatures up to 500 F. In tensile fatigue tests, the creep rate
decreased continuously with a decrease in
the mean free path at all temperatures
while in the stress-rupture test this was
true only at 500 F. In general the ductil-

BROCM, To, J0 Ac MAZZA, AND V. N. WHITTAKER Confd Effect of Dispersion of Alpha, etc,

Structural Changes Caused by Plastic Strain ity was greater in the creep than in the
and by Fatigue in Aluminum-Zinc-Magnesium- corresponding tensile fatigue test. How-
Copper Alloys Corresponding to D.T.D.683 ever, the mode of fracture is primarily
dependent upon temperature and not the
INSTITUTE OF METALS JOURNAL, V. 86, pp.17-23 dispersed phase. At 500 F, the fatigue
September 1957. failure was generally transcrystalline,
at 700 F it was intercrystalline while
In alloys treated to have a U.T.S. of about at 600 F, evidence of both types of fail-
40 tons/in., with an elongation of about 10# ure was observed.

Contfd Structural Changes Caused by, etc.

BROCK, G* W., AND G0 M 0 SINCLAIR
catastrophic softening on certain planes
can be observed in the late stages of both Investigation of the Fatigue Properties
tensile and fatigue tests. This softening of Leaded Alloy Steels
is associated with structural changes such
that the planes can be revealed by etching UNIVERSITT OF ILLINOIS FOR BUREAU OF
polished sections from the interior of spec- ORDNANCE, U.S. OFFICE OF TECHNICAL
imens. The planes are identified as those SERVICES, PB 121834, 57 pp. (March 1957).
upon which extensive slip has occurred.
Possible mechanisms for the formation of
bands of heavy slip in fully hardened alloys
are discussed.
-10-
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BROCH, T., and R, K. HAM BUHLES, H., AND Wo SCHHEIBER
The Hardening and Softening of Metals by Investigation of Some Problems in Fatigue
Cyclic Stressing by Means of the "Staircase« Method of
Testing
PROCEEDINGS OF THE ROYAL SOCIETY, SERIES A
No. 1229s October 1957. ASCHIV FUR DES EISENH(jTTENHESEN, VOLo 28
No0 3, pp 153-156 (March 1957)
Metals subjected to alternating tensile and
compressive stresses give characteristic Authors employ the use of "Staircase" test
stress-strain relationships. Recent studies scheduling to develop damage lines for un-
have shown that the Bauschinger effect in notched and notched rotating-beam speci-
single crystals and the hardening that is mens of GK10 steel. In this program, a
observed during cycling at constant strain specimen was tested at some stress level

Confd The Hardening and Softening, etc.

Cont"d Investigation of Some Problems, etc,
amplitude are closely related to the modes
of deformation of single crystals extended S to a predetermined lifetime, then re-
by means of tensile stresses only. Other tested to failure or runout at the fatigue
observations on stress-strain hysteresis limit o The next specimens were tested at
loops of single crystals have suggested a a stress S +AS cr S -^SS fto the same life-
specific mechanism for the reduction in time), according as to whether the previous
loop width which occurs during continued specimens survived or did not survive the
cycling at low stresses and frequencies. retest at the fatigue limit. This was done
New investigations have been made of the for five predetermined values of lifetime.
hardening produced in annealed polycrystal- Fatigue notch factors are presented.
line copper and aluminum by alternating
stresses applied at a frequency of 100 c^/s 3 tables, 7 figures, 9 references.

° Cont*d The Hardening and Softening, etc. BURNS, ANNE

and of such magnitude as to give complete
fatigue failures in 2 x 10 cycles. It is Fatigue Loadings in Flight-loads in the
shown that the hardened material, as judged Tailplane of a Comet I0
by tensile testing., is quite different from
that produced by unidirectional deformation RAETN STRUGo 222 (ENGLAND) 19 pages
and, in particular, the large temperature- March 1957, and AERONAUTICAL ENGINEERING
dependence of the flow stress suggests that REVIEW (USA) 16, NO. 9, page 136,
an important contribution to hardening a- September 1957.
rises from the production of point defects
during stressing.

BROTZEN, FRANZ R. AND JOHN F. WALLACE BUTLER, J e P.

Fatigue Properties of Gray Iron
The Rehabilitation of Fatigue-Weary
MACHINE DESIGN, ?„ 29, pp. 154-158 Structure
DECEMBER 12, 1957
Endurance limit and endurance ratio$ in- ASTM STP-203, PO 29, 1957
fluence of stress conditions; notch sen-
sitivity; overstressing and understress- BUNYAN, ToW.
ing; effects of surface rolling, surface
finish, structure, composition, section Fatigue Performance of Marine Shafting-
size, heat treatment, and high and low Laboratory and Service Tests
t emperature s. ASTM STP 216, p 59, 1957.
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11 Paper presented at a symposium at the
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BURNS, ANNE BUTLER, J. P.
Fatigue Loadings in Flight; Loads in The Rehabilitation of Fatigue-Weary
the Tailplane and Fin of a Varsity Structure
AERONAUTICAL RESEARCH COUNCIL (ENGLAND)
REPORT No. 256, January 1956. AMERICAN SOCIETY FOR TESTING MATERIALS
Data are presented on the number of load STP, page 29, 1957.
cycles of various sizes occurring in the
tailplane and fin of a Varsity in normal
ground and flight conditions. The con-
ditions include flight in turbulence,

Cont'd Fatigue Loadings in Flight: BUTLER, ROBERT H., ROBERT H. BEAR, and
THOMAS L. CARTER
take-off, landing, taxying, and ground
running of the engines. The relative Effect of Fiber Orientation on Ball Fail-
importance of the loads in the different ures Under Rolling-Contact Conditions.
conditions is illustrated by reference NACA TN 3933, February 1957.
to the loads in a typical flight.
The rolling-contact fatigue spin rig was
used to test balls of a bearing steel at
maximum Hertz stresses of 600,000 to 750,000
(Aircraft Eng.(England) 29, No. 335 psi. The effect of fiber orientation was
page 27, January 1957.) observed with the ball track restricted to

BUTLER AND CARTER s Cont'd Effect of Fiber Orientation, etc.

Stress-Life Relation of the Rolling- passing directly over the poles, coinci-
Contact Fatigue Spin Rig dent with the equator, or randomly around
the ball. The polar areas were found
NACA TN 3930, March 1957 to be weaker in fatigue than the non-
polar areas. This resulted in a much
The rolling-contact fatigue spin rig was greater portion of the failures occurring
used to test balls of a bearing steel in the polar areas than would be expected
at stresses higher than those produced in from a homogeneous material. The early
bearings. Groups of 9/16-inch SAE 52100 failures are discussed.
Grade-1 steel balls lubricated with a

Cont *d Stress-Life Relation of, etc. CALVERT, N.G.

mineral oil were tested at 600,000-psi, Fatigue Tests on Glass-Fibre Reinforced

675,000-psi, and 750,000-psi maximum Plastics
Hertz stress. The balls were tested
at room temperature on fixed tracks THE ENGINEER, VOL 204, page 522
that were randomly oriented to the fiber (October 11, 1957)
direction of the ball. Plain cylinders
of commercial-melt and vacuum-melt Tests in Wohler machine; fatigue
AISI M-l and commercial-melt AISI M-50 strength about 12$ of static strength.
(MV-l) with a bore size ranging from
3.250 to 3.550 inches were used as race
specimens.
-12-
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CARTER, T. L< CHILDS AND IEMCOE
Effect of Lubricant Viscosity on Rolling
Contact Fatigue Life Fatigue Investigation on High Strength
Steel
NACA TN 4101, October 1957
WADC Technical Report 56-205
Rolling contact fatigue spin rig used to ASTIA DOCUMENT N00 AD 110474, July 1957
study life of steel balls lubricated with
paraffin-base mineral oils. AISI M-l balls SAE 4340 steel, heat-treated to 190,000,
tested at 100°F and calculated max.comp 260,000, and 300,000 psi ultimate tensile
Hertz stress of 725 psi longer life observed strength was tested by the increasing
for higfter lubricant viscosity. Life varied load method (similar to Prot's method)
approximately as 002 power of lubricant in axial loading to determine the varia-
viscosity. tion in fatigue properties under each

CAZAUD, R. Contgd Fatigue Investigation on High, etc,

Prestressing Prevents Fatigue Failures of the three mean stress conditions?
from Occurring. 0, 60,000, and 90,000 psi. Conventional
FRANCE INDUSTRIES, NO. 15 (March 1956) S-N curves were determined by axial load
(ENGINEERING DIGEST, VOL 3, No. 1, tests at 190,000 psi ultimate tensile
pp0 22-24, January 1957). strength, under zero mean stress and
90,000 psi mean stress, to provide factors
The principles of setting up residual for adjusting the Prot-type failure stress-
stress patterns to offset the forces es to standard mean endurance limit val-
experienced under working conditions ues. In addition, Prot rotating beam
are outlined. tests were performed at 190,000 psi ul-
timate tensile strength.

Cont'd Prestressing Prevents Fatigue,etc, CINA, Bo

The Effect of Surface Finish on Fatigue
These prestresses can be induced by
mechanical, heat or chemical treatments. METALLURGIA, VOL, 55, pp.H-19
January 1957.
Test results are shown for two aluminum Wohler and Haigh fatigue tests were
alloys and a low-carbon steel. Super- carried out on stable and unstable aus-
ficial hardening of steel is given special tenitic, fully ferritic, and martensi-
attention as the endurance limit can be tic stainless steels, and a low alloy
almost doubled by this treatment steel. The test pieces were prepared
either by mechanical polishing to 000
paper, or by electro-polishing. Some
of the former were subsequently stress-
Cont'd The Effect of Surface Finish, etc.
COFFIN, JR., L.F.
relieved at 650°C. The electro-pol-
Thermal Stress Fatigue ished test pieces gave consistently
lower fatigue limits than the mechanically
PRODUCT ENGINEERING, VOL. 28 polished test pieces indicating a strength-
pp 175-179, June 1957. ening effect in the latter due to cold
work. Less scatter of results was also
Where thermal stresses originate; observed with the electro-polished test
how thermal stress fatigue differs pieces. Electro-polishing gave a smaller
from mechanical fatigue; what design reduction in the Haigh tests, and so
criteria to use. brought the rotating-bending and direct
stress tests more closely into agreement.
Vacuum stress relieving gave results
-13- similar to those obtained by electro-
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polishing.
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 COFFIN, JR., L.iT.
CLAREB80I?GH, L.M., M. E. HARGREAVES,
AND G. W, WEST An Investigation of Thermal-Stress Fatigue
as Related to High Temperature Piping
The Energy Stored in Fatigued Metals Flexibility
ASME TRANSACTIONS, page 1637, October 1957.
ROYAL SOCIETY PROCEEDINGS, VOL. 242,
ser A, pp. 160-166 + 2 plates This paper is a summary report of a co-oper-
October 29, 1957 ative research investigation extending
earlier work on the thermal-stress-fatigue
Determinations of stored energy and hard- resistance of A151 Type 347 stainless steel.
ness for two series of specimens of O.F.H.C, The investigation was to provide additional
Cu fatigued at stresses which give rise qualitative experimental support of the con-
to failure at 2.8 x 10^" cycles in one case cept of fatigue design based on an allowable
and 10 cycles in the other. stress range which is embodied in the ASA-

Contfd The Energy Stored in Fatigued, etc, Contfd An Investigation of Thermal-Stress

B31.1 Code Rules for Piping Flexibility
Design. Two specific objectives were es-
For specimens fatigued at high stress tablished, together with the findings of
the stored energy is released by a com- this research: (a)lnvestigation of the ef-
bination of recovery and recrystallization, fect of cycling which produces tensile
but for specimens fatigued at low stress rather than compressive stress under the
only recovery was observed. hot condition. It was found that there
was no significant difference, (b)Investi-
gation of the effect of reducing the net
mechanical strain range for a given temper-
ature range to a point approaching the de-
sign strains for a piping system.

CORDIANO, H.V. Contfd An Investigation of Thermal-Stress

"While the temperature range was held con-
A Unique Machine for Large Scale Fatigue stant, the trend of reducing the net mech-
Testing anical strain range was to increase the
number of cycles to failure similar to that
ASTM PREPRINT #86c, ANNUAL MEETING 1957 obtained when the net mechanical strain
The fatigue machine described operates on range was reduced by lowering the tempera-
the principle of the dynamic vibration ture range under full constraint. In
absorber. At the natural frequency of the addition, for the same mechanical strain
vibration absorber the damper mass vibrates range, widening the temperature range de-
creased the number of cvcles to failure.
in such a manner that the force of the main
mass is zero, and the strain in the damper Report contains graphs, tabular data,
spring is proportional to the exciting force and photomicrographs.

Contfd A Unique Machine for Large, etc. COTTRELL, A. H., F.R.S., AND D. HULL
In the actual machine, the exciting force is Extrusion and Intrusion by Cyclic Slip
developed by two sets of rotating eccentric in Copper
disks, 180° out of phase, and the absorber
consists of a weighted test specimen sub- PROCEEDINGS OF THE ROYAL SOCIETY, SERIES
jected to bending loads. Uniform bending
moment is applied over a 40 in.span, and the A, No. 1229, October 1957.
capacity is 400,000 in.lb. Tests have
been made on riveted and welded joints with
various steel plates at a frequency of about
300 cpm. The results were generally in agree-
ment with work reported by other investiga-
tors . -14-
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COULSHED, W.F., AND D. S. MORE CUMMINGS, H.N., F. B. STOLEN AND •
W. C. SCHOLTE
A Versatile Control Equipment for
Fatigue Testing Relation of Inclusions to the Fatigue
Properties of SAE 4340 Steel
AIRCRAFT ENGINEERING, VOL. XHX TRANSACTIONS, AMERICAN SOCIETY FOR METALS
No. 341, pp. 219-221 July 1957 VOL.XLDC, pp 432-516, 1957
A description of an electronic control From studies on more than a thousand un-
unit for fluctuating load cycles. notched R.R.Moore fatigue specimens, the
authors have established a trend in the
1 photograph, 7 diagrams. relation between the size and distribution
of inclusions and the fatigue life of SAE
4340 steel heat treated to three different

CUMMINGS, H. N., F. B. STOLEN AND Cont*d Relation of Inclusions to the, etc.

W. C. SCHULTE
tensile strength levels. The first micro-
Investigation of Materials Fatigue Problems crack was always found to be associated
with a large inclusion at or slightly be-
CURTIS-WRIGHT CORP, WRIGHT AIR DEVELOP- low the surface, regardless of stress level,
MENT CENTER, WADC TECH. REPORT 56-611 but the final fracture was not always as-
March 1957 sociated with the first crack. At low
stresses, fatigue appears to start at some
The studies of high-hardness steels that single dominant inclusion while at high
were begun Contract AF 33(6l6)-493 were stresses not only is the dominant inclu-
continued. S-N curves were obtained for sion, but also a number of smaller inclu-
SAE 4340 air-melted steel of 230 ksi Ufe and sions, a factor in determining fatigue life.
vacuum melted steel of 190 ksi UTS.

Contfd Investigation of Materials, etc.

Gont'd Relation of Inclusions to the, etc,
Several steels of 300 ksi UTS were investi-
gated by Prot tests, and S-N curves were ob-
tained for a 4350 steel of the same UTS. This is further born out by tests on
Studies of the relation of non-metallic vacuum melted steel of the same composi-
inclusions to fatigue life and strength tion. Here, in the absence of larger
of the steels were continued and explora- inclusions, the high strength fatigue life
tory studies were made of crack initiation is only slightly increased, while the low
and propagation. The applicability of the strength fatigue life is substantially
Prot method of testing to four non-ferrous increased*
metals was also included in the work done
under the present contract.

CUTHBERTSON, J.W. DE LEIRIS, H.

Fatigue Properties of Brasses, Bronzes Annual Report of Commission XIII:
and Bearing Metals. Fatigue Testing
METAL TREATMENT AND DROP FORGING, VOL 24, BRITISH WELDING JOURNAL (ENGLAND) 4,
pp 89-92, March 1957 and April 1957 p.159. No. 5, PP 229-230, May 1957
Service requirements of bearing alloys
and the mechanism by which bearings fail
through fatigue. Fatigue characteristics
of various alloys. Studies of backed and
unbacked bearings; assessment of fatigue
resistance; raising the fatigue resistance
of various bearing alloys.
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 DE'LEIRIS, H. DIMOL, L., F. HEBHANT, AND H. LOUIS

Fatigue Testing Fatigue Tests on Welded Assemblies made

up of Two Perpendicular I DIN 40 Beams
SHEET METAL INDUSTRY (ENGLAND) 34,
No. 361 Typewritten document, 14 pages
BIBLIOGRAPHICAL BULLETIN FOR WELDING
PP 367-369, May 1957 (FRANCE) 9, No. 4/6, page 94E,
April-June 1957.

DE LEIRIS, H, AND V. CORFA DEVELAY, R. AND H. RICHAUD

Identification of the Starting Point The Effect of Surface Treatment on the
of Fatigue Cracks (identification des amorces Fatigue Resistance of Some Titanium and
de fissures de fatigue). Aluminum Alloys (Influence des traitments
de surface sur la resistance a la fatigue
REV, ALUMINUM (FRANCE) 34, de quelques alliages de Titane et alliages
No. 246, page 794, September 1957 dlAluminum
REV. ALUMINUM (FRANCE) 34,
Noo 246, page 792, September 1957

D1MER, L. J« DITTMAR, CHARLES B., G. WILLIAM BAUER,

AND DILLON EVERS
Interrelation of Fatigue Cracking, Damping,
and Notch Sensitivity The Effect of Miscrostructural Variables
and Interstitial Elements on the Fatigue
WADC TECHNICAL REPORT NO. 56-408 Behavior of Titanium and Commercial
March 1957 Titanium Alloys
WRIGHT AIR DEVELOPMENT CENTER, MATERIALS
Materials -N-155, two steels, gray iron, LABORATORY, WADC TECHNICAL REPORT 56-304,
2024-T4, J-l Mg. Alloy. Coating with
white lead and oil was best method of 83 p. January 1957 (TL507 Un3.l8w Vis.)
crack detection for smooth specimens, Microstructure was found to have little ef-

Cont'd Interrelation of Fatigue Crack, etc, Cont'd The Effect of Microstructure, etc,

deflection was best for notched ones*

Damping and dynamic modulus were measured. feet on the endurance limit of Ti-5Al-
Notch sensitivity approached 1 when cal- 2.5Sn, n-6Al-4V, and Ti-3Mh unless the
culated on basis of first crack. structure was extremely coarsened or
embrittled.
values were often less than 0.02 for

Kt-3.9

-16-
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 ELSESSERo T.M»
DORING, WERNER Influence of Repeated Bending Loads on
Biaxial Residual Stresses in Shot-Peened
Aging and Fatigue of Steels Plates.
EISENBAHNTECHNISCHE RUNDSCHAU, VOL 6, ASME TRANSACTIONS, November 1957
pp. 306-313, August 1957
The futility of shot-peening certain members
to increase their fatigue strength may be
explained by the reduction of the initial
residual stresses which increased ttuiibers
of repeated loads. The purpose of this
investigation was to determine the changes
in the biaxial residual stresses, induced

DYRKACZ, W.W. AND B. E. REYNOLDS Cont'd Influence of Repeated Bending, etc.

by shot-peening, in steel plates subjected
Vacuum Melted Alloys for Forged Parts to cyclic bending loads. The plates were
sectioned by etching, and curvature meas-
PRODUCT ENGINEERING, pp.143-145 urements were made to evaluate the resid-
February 1957. ual-stress distributions in the region of
the peened surface. The residual stresses
Advantages and limitations of consumable were found to "fade" or decrease to at
electrode and induction heating processes least 50 per cent of their initial value
for M-252, waspaloy and A-286; effect on in 10,200 load cycles in the medium-hard
cleanliness, segregation, and elevated (SAE 4340) steel investigated.
'temperature properties (including fatigue); Report contains tabulated data, graphs, and
relative costs and growing fields of use. specimen and apparatus detail diagrams.

EATON, F. C. ERRA, A.
Fatigue Tests of Large Alloy Steel Shafts
Note on the Concentration of Stresses
AMERICAN SOCIETY FOR TESTING MATERIALS in Elliptical Fillets.
Preprint No.86a, 1957, 8 p.(TA401 Am35p Vis)
Tests were made on 9-in. diameter unnotched METALLURGIA ITALIANA, VOL049,
Ni-Cr-Mo alloy shafts, 8j in. diameter page 509, JuOy 1957
notched shafts, and on 0.469 in.diameter
specimens removed from one of the large Determination of stress concentration
shafts broken. Data indicates a considerably factor by photoelasticity and fatigue
lower fatigue limit for the large diameter tests.
unnotched shafts than for the smaller spec-
imens .

ECKERT, E. J. FAQUET, J.
Torsional Fatigue Testing of Axle Shafts Metallurgical Problems Associated With
Aeronautical Progress (Problemes poses
AMERICAN SOCIETY FOR TESTING MATERIALS, a la metallurgie par 1'aeronautque)
Preprint No. 86b, 1957, 13 p.(TA401 Am35p Vis)
REV. METALLURGIE (FRANCE) 54,
Design, build-up, and running of the No. 7, PP 555-568, July 1957
testing machines. Effect of various
surface conditions and hardness.

-17-
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FELD, JACOB FERRO, A., AND U. ROSSETTI
A contribution to the study of Fatigue
Failures of Concrete Structures of Materials (Duralumin and Steel) by
Progressive-Charge Tests
AMERICAN CONCRETE INSTITUTE JOURNAL,
VOL 29, pp 449-470, December 1957 PROG. COLLOQUIUM ON FATIGUE,STOCKHOLM,
(SWEDEN) pp.24-34, May 1955, 1956
A historical survey of concrete failures METAL. ABSTRACTS (ENGLAND) 24, Part 8
of the last half century in the U.S., page 619, April 1957
grouped according to their major causes: Ferro and Rosetti report fatigue tests,
design, deficiency, drafting and detail- with both constant and progressive loads,
ing errors, concrete mix, supervision Progressive loading leads to longer
lives than would be calculated from the

sCont'd A Contribution to the Study, etc.

Cont!d Failures of Concrete Structures
constant-load tests on the hypothesis of cumu-
lative damage, and this measures the ef-
omission^ frost protection defects, fect of understressing; for steel this
bearing wall deficiency, foundation effect shows up only at low rates of load
deficiency, faulty erection techniques, increase, but for Duralumin only at high
temperature and shrinkage, secondary rates. In extrapolating the breaking
stresses, and inadequate formwork. loads found in progressive loading to zero
rate to obtain the fatigue limit, a better
straight line is obtained by plotting
against the cube root, rather than the sc.
root of the rate increase; this is because
for both steel and duralumin, in constant-
load tests, the number of cycles to fail-

FENNER, AoJ. AND J. E. FIELD c Contfd A Contribution to the Study, etc.

Effect of Fretting Corrosion on the ure al/(load-fatigue limit)2.
Fatigue Failure of 17S Alloy Under
Direct Stress (Influence de la Corro- For Dualumin, reliable values for the
sion de frottement sur la rupture par fatigue limit can be reduced from pro-
Fatigue Sous Uontrainte Directe D*un gressive-load tests if these include
Duralumin) rates of increase down to
REV. ALUMINUM (FRANCE) 34 <LO-6kg./mm./cycle.
No. 246, page 792, September 1957

FERRO, A., AND R. COLOMBO

A New Analytical Treatment of the S-N FINNEY, J. M.
Curves, Based on Purely Probabilistic
Consideration. (Sulla teoria probabilis- The Effect of Pickling and Anodising
tica della fatica). on the Fatigue Properties of 2L40 and
METALLURGIA ITALIANA, VOL. 49, July 1957 DTD 683 Aluminum Alloys.
pp.518-522.
AERONAUTICAL RESEARCH LABORATORIES
Re-examination is made of Freudenthal's (AUSTRALIA), July 1957
theory of fatigue occurrences in metals,
for which assumption is made that fatigue
cycles, taken singularly or grouped, repre-
sent independent causes of failure occur-
ring at the end of N alterations. -18-
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FINDLEY,.W.N. FISHER, tf. A. P.

Fatigue of Metals Under Combinations of Substantiation of Safe Fatigue Life

Stresses for Rotorcraft

ASME TRANSACTIONS, p.1337, August 1957 AERONAUTIC RESEARCH COUNCIL

GREAT BRITAIN, 1957
Analysis of available information suggests
that the phenomenon of fatigue of materials This paper gives a comprehensive system
results primarily from alternating shearing of development and testing to substan-
stress producing cracks along shear planes, tiate rotorcraft for fatigue.
and that the resistance to fatigue cracking
is influenced by other factors.

Cont*d Fatigue of Metals Under, etc.

FOLDES, G.
Some of these factors are changes in struc-
ture of the material resulting from plastic Fatigue Testing of Sheet Metal
and elastic stressing as well as heat treat-
ment | the mode of crack propagation and SHEET METAL INDUSTRY, VOL. 34
complementary normal stress on planes of page 749, October 1957
shear stress„ Several theories of failure
under combined stress are examined and mod- In Vibrophore machine with special
ified to account for observed facts. A grips.
general design expression is proposed* The
^influence of mean stress (including extreme
'compression), yielding, complementary normal
stress, and anistropy are considered. Graphs,
photos of specimen fracture and testing appar,

FINK* tf. L. FORD, Do G., J. L. KEPERT

Ultrasonic Testing of Aluminum Alloys Estimation of Fatigue Life of Structure
AMERICAN SOCIETY FOR TESTING MATERIALS from Observed Damage
BULLETIN, No. 226, pp.36-41, Dec. 1957
A.R,L. NOTE S.M0 232, July 1956
Effect of discontinuities revealed by ultra- JOURNAL ROYAL AERONAUTICAL SOCIETY,
sonic testing, on the fatigue life of cer- AUSTRALIA 6l, No. 556, p.294, April 1957
tain aluminum alloys is discussed. Lug- In estimating the residual life of an
.type specimens from a 7075 alloy forging unbroken fatigue specimen, a procedure
were tested under cyclic tension stress based on comparison of crack propaga-
(minimum stress zero). Discontinuities tion rates has been found to give re-
parallel to the stress direction had no

Cont'd Ultrasonic Testing of Aluminum,etc iCont'd Estimation of Fatigue Life, etc,

liable results, A statistical method
effect on the fatigue behavior, whereas using maximum likelihood estimators
even small discontinuities perpendicular showed reasonable agreement. The desire-
to this direction could initiate fatigue ability of using this method as a check
cracks depending upon their location in on the estimates has been discussed.
relation to a loading pin-hole.

-19-
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 FORREST, G. FORREST, P. G.
Fatigue Properties of Aluminum Alloys Speed Effect in Fatigue

SHEET METAL INDUSTRIES, VOL. 34, PROCEEDINGS ROYAL SOCIETY, Ser. A,

pp 831-845, November 1957 ENGLAND 242, No, 1229, pp 223-227,
October 29, 1957.
A review of the literature. Presents It is usually found that the fatigue
fatigue curves for a variety of aluminum strength of metals is slightly reduced
alloys and the effects of heat treatment, by decreasing the cyclic speed, the
work hardening, aging, notches, mean reduction becoming greater with.in-
stress, residual stress, surface finish, crease in temperature.

Cont*d Fatigue Properties of Aluminum,etc, ;Cont»d Speed Effect in Fatigue

However, this usual speed effect is
corrosion and metallurgical factors such reversed for mild steel at temperatures
as ingot size, grain size, test direction, between 200 and 300o C. In this tem-
heat treatment and mechanical working. perature range the fatigue strength is
considerably greater at 10 c./min.
than at 2000 c./min„ It is thought
that this behavior is caused by strain-
ageing. (Author's summary).

FORREST, G. FORSYTE, P.J.E.

Slip-Band Damage and Extrusion
The Effect of Fatigue Notches, Surface
Finishes, etc. ROYAL SOCIETY PROCEEDINGS, v. 242,
sercA, pp. 198-202 + 4 plates'1*
THE FATIGUE OF METALS, INST. OF October 29, 1957
METALLURGISTS, ENGLAND, 1956 Slip-band extrusions in a fatigued Al-4#
AUSTRALASIAN ENGINEER, AUSTRALIA 49, Cu alloy are less than 00ln thick, and
No. 3, page 68, March 7, 1957 often occur only along short lengths of
the active slip band. Thickness of such
a "ribbon" varies with different materials
and fatigue conditions,. The slip process
which results in extrusion appears to be

PORSYTH, P.JJ5. ;Contf d Slip-Band Damage and Extrusion

Some Observations on the Nature of Fatigue
Damage in the nature of reverse glide in which
two sets of planes near to one another
PHILOSOPHICAL MAGAZINE, V.2, ser. 8 slip in preferred directions. Confine-
pp.437-440 * 2 plates, April 1957 ment of slip to a few active planes as
Fatigue stresses produce damage in such mat- occurs in most Al alloys is due to some
erials as Al 7*5# Zn 2«5# Mg in the form of localized softening process. These pro-
persistent bands which at an advanced stage cesses are local recrystallization, ag-
contains rows of holes. The bands can be re- ing, and a combination of both effects.
moved by heat treatment, but the holes are In pure Al some Al alloys, holes may be
not healed. Slip band extrusion occurs a- observed along the slip bands. In AgCl
long these damaged planes and the presence slip bands or striations which extrude
of the holes may on occasion cause very fine -20- also show crevices where retraction has
extrusions in the
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FQRSYTH?, P.J.E. AND CoAoSTUHBINGTON FOSTER, Bo K«
The Mechanism of Fatigue Failure in Some The Propagation of Fatigue Damage Measured
Binary and Ternary Aluminum Alloys by Periodical Polishing
JOURNAL INST. OF METALS, VOL 85, AIRCRAFT ENGINEERING, VOL XXIX No. 341
PP.393-343* 1956-1957 July 1957
The fatigue process in a number of alumin- By means of an electron microscope, surface
um alloys was found to be one of depletion changes may be observed on metals in fati-
of solute atoms in localized regions under gue long before a crack becomes apparent.
the action of cyclic stresses. The deple- Removal of the damage front by electrolytic
tion or overaging produced soft spots in polishing or some mechanical means causes
the structures in which most of the subse- the specimen to behave as if it were a
quent plastic deformation was concentrated. virgin specimen.

gCont'd The Mechanism of Fatigue Failure,etc,

tCont'd The Propagation of Fatigue Damage,etc
It appeared that the temperature range
was important in determining whether the The author conducted tests on mild steel
depleted zones were trans- or intercrystal- specimen approximately 8" long x l/2n dia.
line and subsequent fatigue cracks followed loaded by a rotating cantilever machine
these paths. A crack, once started might running at 1500 RFM. Removing .0005 in-
by virtue of the heavy stress concentra- from the damaged surface at intervals
tion, produce its own depleted zone ahead of 10* cycles was sufficient to prolong
of the root, and could thus progress with- the life of the specimen to three times
out reference to existing soft spots. its expected life*
4 references, 4 photographs, 14 diagrams

FOSS3EZ, Jo, R.SITTE AND S0ZIEMBINSKI FOSTER, Ho W«

On the Resistance of Metals to Repeated
Shock (FR.) Fatigue Testing of Airframe Structural
Components
CCMPTES RENDUS, VOL. 244, pp 1008-1011
February 18, 1957. AMERICAN SOCIETY FOR TESTING MATERIALS
Experiments on steels successive sharp ten- PREPRINT ANNUAL MEETING, 1957
sile stresses produced by periodically ex-
cited electromagnet, intensity measured by The considerations involved in preparing
a piezo-electric quartz dynamometer. In- programmes of simulated service fatigue
fluence of frequency of shock; pseudo- tests of airframe components are discussed.
aging of the metals; influence of elastic Tjrpical components used for illustrative
shocks. purposes are the primary wing surface

FRANKLIN, R.J,F. sCent'd Fatigue Testing of Airframe, etc,

Engineering Research at East Kilbride
structure, landing gear, and secondary
METAL INDUSTRY, V.91, PP 265-269 and equipment structure subjected to very
September 27, 1957 high cycle loadings.
Review of work in progress at the Mech- A 500,000 Ib fatigue testing machine is
anical Engineering Research Laboratory briefly described, and the reliability
at Glasgow, Scotland. Current projects of data which may be obtained from tests
include studies of fatigue cracks, of a single component is discussed.
strength of pin-joints, creep under com-
plex stress, and design of extrusion dies.

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 FREUDENTtfAL, A.M. FRITH, PoH.
The Safety of Aircraft Structures Properties of Wrought and Cast Aluminum
and Magnesium Alloys, at Atmospheric and
WADC TECHNICAL REPORT 57-131 Elevated Temperatures
ASTIA DOCUMENT No.AD 130910, July 1957 Book published for Ministry of Supply by
The difference in the approach to the HER MAJESTY'S STATIONERY OFFICE, LONDON,
ENGLAND, 178 pages.
concept of safety for ultimate strength
and for fatigue is discussed, considering The test at atmospheric and elevated tem-
recent development in fatigue research, peratures up to 350 °C, included fatigue,
particularly the results of fatigue tests tensile, expansion and conductivity,
under random loading, and methods of safe- whilst density and hardness tests were
ty analysis for both conditions are pro- carried out at atmospheric temperature only.
jposedo The hardness tests were made after soaking

Cont'd Properties of Wrought and Cast, etc,

.FREUDENTHAL, A0M.
in the unstressed condition at elevated
Fatigue in Aircraft Structures temperatures for various times up to 1000
hourso The total number of alloys tested
AIRCRAFT ENGINEER, ENGLAND 29, was forty six, eighteen being wrought and
No. 342, page 252, August 1957. the remainder sand cast. For the fatigue
tests, standard or notched test pieces were
used for the wrought alumimim alloys, and
standard or fillet test pieces for the re-
maining materials, the tests being carried
out with a reversed bending stress or with
a bending stress superimposed on a static
tensile stress. Fatigue tests were also
made with standard test pieces on wrought

FREUDENTHAL, A.M. AND R.A.HELLER sCont'd Properties of Wrought and Cast, etc,
Cumulative Fatigue Damage of Aircraft aluminum alloys at atmospheric temperature,
Structural Materials after soaking in the stressed or unstressed
Part 2s 2024 and 7075 Aluminum Alloy condition for 1000 hours at various ele-
Additional Data and Evaluation vated temperatureso In addition, creep
tests were made on wrought aluminum alloys
U.S. DEPT. OF COMMERCE PB 121909, at elevated temperatures, and the metallo-
27 pages, October 1956. AMERICAN METAL graphic tests carried out on these materials
MARKET, USA 64, No. 131, page 11, before and on completion of the creep and
July 10, 1957o fatigue testso These tests showed that the
Tests were conducted on 20 unnotched speci- material with the best fatigue properties
mens of 2024 and 7075 aluminum alloy to for a certain temperature, did not necess-
determine the effect on fatigue life of arily have good creep and tensile proper-

•Contfd Properties of Wrought and Cast, etc.

Cont'd Cumulative Fatigue Damage, etc.
ties at that same temperaturee Therefore,
of randomly varying stress amplitudes repre- in order to use elevated temperature data
senting gust or manoeuvre load sequences for design purposes it is essential to
encountered during flights. A non-linear know the operating temperature fairly ac-
cumulative damage theory was developed that curately, and also to know whether the
approximated test results reasonably well major operating stresses will produce a
for unnotched specimens used in the tests. fatigue, creep, or tensile failure.
A comparison of data seemed to justify the The published data on the properties of
tentative conclusion that with decreasing wrought and cast aluminum and magnesium
severity of the load distribution the com- alloys at atmospheric and elevated temper-
parative fatigue performance of alloy 7075 atures, are given in tabular form, and
improves, but for increasingly severe dis- compared with the results obtained in
tribution 2024Int'lis
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FRITH, P*H. FROST, N.E* AND C. E0 PHILLIPS
Some Observations on the Spread of
Effect of Temperature on Fatigue Properties Fatigue Cracks
Books THE FATIGUE OF METALS PROCEEDINGS ROYAL SOCIETY, Series A
INST. OF METALLURGISTS, ENGLAND, 1956 ENGLAND 242, No. 1229, pp 216-221,
AUSTRALASIAN ENGINEER, AUSTRALIA 49, October 29, 1957.
No« 3, page 68, March 7, 1957
This paper considers fatigue cracks after
the stage of initiation and refers mainly
to conditions under which continuous propa-
gation does not oc-cur. Examples of non-
propagating cracks in notched round bars,

TO)ST, No E, ;Contfd Some Observations, etc.

Fatigue Strength of Specimens Containing plates and thin sheets are given| the role
Preformed Fatigue Cracks of such cracks in accounting for much of
the difference between theoretical and
ENGINEER, v.2035 pp.864-867, June 7, 1957 experimental fatigue stress-concentration
values is emphasized„ The discontinuous
The fatigue limits of pre-cracked cylind- nature of growth of slowly growing cracks
rical specimens obtained under a repeated is showno The maximum length of non-propa-
tension loading cycle with a minimum ten- gating cracks varies with the material;
sile stress of one ton per sq.in. ares mild steel gives longer ones than aluminum
mild steel, 1 to 12 tons per sq. in.; alloy L 65, whereas so far they have not
, Ni-Cr steel, 1 to 15 tons per sq.in.; Al been found at all in copper (although
alloy 1 to 5<>5 tons per sq. in. very slow rates of growth are recorded.)

FROST, N.Eo GATEWOOD, B. E.

Thermal Stresses, With Applications to
Non-Propagating Cracks in Vee-Notched Airplanes, Missiles, Turbines5 and
Specimens Subject to Fatigue Loading. Nuclear Reactors0
AERONAUTICAL QUARTERLY, V08, pp 1-20 MCGRAfeT-HILL, NEW YORE, p 232, 1957
+ 4 plates, February 1957 (TA405 G22t)0
All phases of the analysis and design of
Reversed direct stress and rotating bend- structures at elevated temperatures are
ing fatigue tests were carried out on spec- covered, including temperature distribution,
imens of Al alloy, Ni-Cr steel and mild elastic and inelastic thermal stresses,
steel. combined applied and thermal stresses,
allowable stressed of various materials.

FROST, N.Eo AND D. S0 DUGDALE GASSNER, E.

Fatigue Tests on Notched Mild Steel Fatigue Strength Under Variable Stress
Plates With Measurements of Fatigue
Cracks PROCEEDINGS COLOQUIUM ON FATIGUE,
STOCKHOLM, SWEDEN, pp 63-64 in May 1955,
JOURNAL OF THE MECHANICS AND PHYSICS 1956
OF SOLIDS, V.5, No. 3, pp 182-192 + METALLURY ABSTRACTS, ENGLAND 24, Part 8
1 plate, 1957. page 658, April 1957.
Circumstances for obtaining no cracks,
non-propagating cracks, and complete
failure were determined in terms of root
radius, mean stress, and stress range.
-23-
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 GATTO, F. GATTO, F.
New Statistical Methods Applied to the
Influence of Specimen Shape on the Analysis of Fatigue Data
Fatigue Resistance of Al-Zn-MgCu Alloy
(Ergal 65TA). New Studies (Italian). PROCEEDINGS COLLOQUIUM ON FATIGUE,
STOCKHOLM, SWEDEN, in May 1955,
ALLtJMINIO, VOLo 26, March 1957 pp 66-76, 1956.
METAL.ABSTRACTS, ENGLAND 24, Part 8
Toroidal and Cylindrical specimens tested; page 659, April 1957
rotary bending strength was not appreci- The author recommends a re-arrangement
ably influenced by shape of specimens. method for drawing the curve of best
fit through data on fatigue life as a
function of stress amplitude. The method
is applied to data on Al-Zn-Cu-Mg alloys.

^GATTO, F. GATTO, Fo
Influence of the Shape of Samples on the Statistical Analysis and Fatigue Data
Fatigue Resistance of Peraluman 50 Alloy. From Testing Aeronautical Materials
(French) Surles methodes d1analyse stat-
MXUMINIO, VOL. 24, June 1957 istique des Resultats des Essais de Fatigue
Fatigue tests under rotating bending loads Effectues sur des Materiaux de l!Aeronautique
were carried out to determine differences METAUX, CORROSION-INDUSTRIES, V.32,
between results obtained using cylindrical pp 18-37, January 1957
sampleso For the Peraluman 50 (5 per cent Applications and characteristics of statis-
Mg aluminum alloy) a difference of 1.0 kg tical methods used in studying fatigue data.
per sq. mm of the fatigue limit, equal to A variant of the "Staircase" methods and
*6 per cent was observed. two new rapid procedures are offered for
data classification and determination of
the frequency curve.

GATTO, F. GEBHARDT ERICH AND BEYER HORST

On Structural Transformations of Aluminum The Effect of Wetting Agents on the Cor-
Alloys During Fatigue Tests (Italian) rosion Properties of Aluminum-75& Magnes-
Sui Cambiamenti Strutturali Nelle Leghe ium Alloys, With Special Regard to Cor-
di AHnainio Durante le Prove di Fatica. rosion Fatigue (Einfluss von Netzmitteln
auf die Korrosion von AlMg7 Unter Besonderer
AELUMINIO, V 26, pp.315-317, July-Aug.1957 Berucksichtigung der Ermudungskorrosion)
Tests on notched samples under rotary bend- Z.METALLKUNDE (Germany) 48, No. 5
ing loads confirm that fatigue behavior pp 232-240, May 1957
of Al-Cu-Mg alloys is determined by the
precipitation of Cu0 A new possible mech- Wire made of aluminum alloys containing
anism of the "size effect" in fatigue 605$ mmagnesium, 0.35$ iron, 0.2# silicon,
tests is also indicated. 0015/£ manganese with minute quantities of

GATTO, F. Cont!d The Effect of Wetting Agents, etc

Influence of Heat Treatment on the Fatigue
Resistance of Ergal Alloy copper and zinc, was made susceptible to
stress corrosion by the application of
ALLUMINIO, VOL.26, pp.463-467, Nov. 1957 an appropriate heat treatment. Corrosion
Test of aluminum alloy in different heat characteristics of samples thus prepared
treated states showed that the average were tested in various agressive media
fatigue resistance under rotary bending to which wetting agents in a proportion
is not appreciably affected by hardening of 002$ were added. The experiments in-
or aging cqnditions; that variations in cluded repeated immersion, stress corro-
resistances are linked to interaction be- sion and corrosion fatigue tests. Pro-
tween interval stresses produced during cedure and equipment are described. The
hardening and method of artificial aging. results obtained are of great complexity
-^4- and show that wetting agents may either
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GILBERT, G.N.J. AND K. B. PAIMER GLCWACKI, Zo
Tensile and Fatigue Tests on Normalized Effect of the Plastic Properties of the
Pearlitic Nodular Irons Strands on the Fatigue Resistance of
Wire Ropes (influence des Characteris-
BRITISH CAST IRON RESEARCH ASSOCIATION tiques plastiques des fils sur la Re-
JOURNAL OF RESEARCH AND DEVELOPMENT, V.6 sistance a la Fatigue des Cables.
pp498-504 + 4 Plates, February 1957
HUTNICKY, POLAND, 13, No. 9 pp 336-339,
Normalizing is shown to improve proof 1956 and KEV. METALLURGY, FRANCE, 54,
stress, tensile strength, hardness, No. 8, pp 284-286, August 1957.
and elongation.

GIRARD, F. AND G. VIDAL GOHN, GJU

Fatigue, Creep and Relaxation in Metals
Fatigue Failure of SI? Alloy Under Tensile-
Coinpressive Load Alternating at 87,000 C/sec, BELT. LABORATORY RECORD, VOL. 35, June 1957
(Ruptures par fatigue d*un Duralumin en If the stress conditions are known and
tract5.on-conipr*ession a 87,000 alternaces can be accurately determined by analysis
par seconde) and from photographic studies, designs
can be made that will be influencing data
PAPER presented at the FALL METALLURGICAL on items relatively free from fatigue
CONVENTION, PARIS, FRANCE, October 1957. failure,. Notes on various factors influ-
encing these deterioration processes.
Test equipment for studying fatigue behavior
of metals under tensile and compressive
loads, alternating at a rate of 87,000

Qcnt,yd Fatigue Failure of S 17 Alloy, etc, HAHN, K. F. AND Ho D. STEFFENS

Fatigue
Studies on Bonded Aluminum Structural Parts
per second, is described. ALUMINUM, VOL033, PP 783-788,, December 1957
The apparatus embodies piesoelectric
transducers0 Results of tests carried The behavior of bonded extruded sections at
out on an alumiT^jm-A^ copper-magnesium high loads were studied on fatigue testing
alloy and also on various magnesium machine (rotating bending) on specimens
alloys, are reported. (REV. ALUMINUM, one meter long. Use of flexible interlayers
FRANCE 34, No. 246, page 792, Sept. 1957. gives higher fatigue limits than straight
bonding or riveting,. Prevention of sudden
changes in resistance moment under flexure
is needed when shaping parts to be bonded.

GLIKMAN, L.A. AND A. N. BABAEV HANSTOCK, R. F.

Detection of Fatigue in Metals
Fatigue Strength of Specimens Built up
for Automatic Submerged Arc Welding (Rus.) BRITISH JOURNAL OF APPLIED PHYSICS,
Ustalostnaia Prochnost1 obraztsov, naplav- Supplement No.6, Physics of Non-Destruc-
lennykh Avtomaticheskoi Svarkoi Pod tive Testing, 1957
Fliusom. Brief review of fatigue and methods em-
METALLOVEDENIE I OBRABOTKA METALLOV ployed or suggested for examining its
development„ Primary consideration is
No. 10, pp 37-43 + 1 plate, October 1957 the assessment of the potential value
Effect of preheating temperature and joint of these methods as primitive non-de-
geometry on amount and distribution of structive tests to reveal fatigue prior
residual stresses,, Materials, methods, and to development of serious structural
results
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HAMILTON j, B.M. HARPER, R.H.T.
Fatigue in Mining and Construction Equipment
Fatigue in Aircraft Structures
CANADIAN MINING AND METALLURGICAL BULLETIN
Volo 50, pp 717-724, December 1957 THE NEW SCIENTIST, ENGLAND 2, No0 33
Fatigue failures occur in load carrying pp 23-25, July 4, 1957.
members of machine parts when they are
subjected to alternating or cyclic stresses.
Fatigue is, therefore, most commonly found
in moving parts which may become deflected
due to overloading and poor alignment.

Contfd Fatigue in Mining, etc, HARTMAN, A. AND F, A. JACOBS

The Fatigue Strength at Fluctuating Tension
(R = 0.1) of Redux Bonded 75S-T Clad Simple
However,, intermittent shock loading Lap Joints from -45°C to + 80°C.
or vibration can also contribute to
fatigue failure in both moving and NLL, NETHERLANDS, REPORT N00M 2016,
stationary parts. 26 pages, August 1956
Fatigue tests to determine the influence
on the fatigue strength of Redux-bonded
joints were carried out. The adhesive is
cured for half an hour at either 145°C or
l60°C<> The results indicate that low tem-
peratures have a favorable influence on

HARDRATH5 HERBERT F., AND RICHARD E.WHAIEY ;Confd The Fatigue Strength, etc.
Fatigne-C:?ask Propagation and Residual fatigue strengtho If the adhesive is
Static Strength of Built-up Structures. cured for half an hour at 160°C, an in-
crease in temperature from 20°C to 50°C
NACA TN 4012, &Xv :.°57 does not have any influence on fatigue
strength. At 80°C joints cured at 145°C
Crack-propagation and static-strength have a low fatigue strength. At 80°C the
tests in several types of built-up specimens adhesive is unstable and continues to
and full-scale wings are reviewed. The harden. This has a favorable influence
.results, to date, indicate that the rate on the properties at elevated temperatures
of crack propagation is influenced strong- the strength at room temperature is not
ly by the mode of connecting the skin to impaired.
stringers and by the proportions of areas AERONAUTICAL ENGINEER REV, USA 16, No.5
page 191, May 1957.
g Gont ' d Fatigue-Crack Propagation, etc. HEDGES, E.S.
New Developments in Aluminum-Tin Alloys
of the skin and stringers. The analysis
of residual static strength of complex ALUMINUM, page 318, May 1957.
structures indicates the feasibility of Increased demands on bearings reveal lim-
applying simple methods, but the results itations of conventional metals» Al-Sn alloys
are subject to questions regarding the combine good running properties of Sn-base
redistribution of loads, interactions metals with high endurance of leaded
between various members, and such seem- bronzes and can be fitted to unhardened
ingly trivial considerations as whether steel shafts* They must have fine grain
or not a crack terminates at a rivet. size. If used on steel shell base, must
be fabricated so there is no differential
-26- elongation of mating surface. Practical
tests show great superiority.
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HEMPEL, M. HMPEL, M., A. KOCHENDORFER AND ,
E. HILLNHAQEN
High Temperature Fatigue Tests The Influence of Crystal Orientation
on Development of Slip Lines at the
ARCHIV FflR DAS EISENHUTTENWESEN, Surface of CX-Iron Single Crystal
GERMANY, 1957 and THE ENGINEER, Specimens loaded in reversed bending
ENGLAND 204, No.5307, pp 450-451 ARCHIV J$R DAS EISENfrfhTENWESEN, VOL 28,
September 27, 1957. No. 8, pp 433-444, August 1957
Bending fatigue tests were made on mech-
anically polished flat specimens of
OC-iron. Metallographic studies were
performed to determine the development

HEMPEL, MAX Contfddd The Influence of Crystal, etc.

Behavior of Heat Resistant Steels in Long- of slip lines and also their location and
Time Creep Tests at 500OC to 700°C, Part VII. pattern in respect to the crystal orienta-
Fatigue Tests at 500°C to 700°C of Ferritic tion.
and Austenitic Steels It was found the slip mechanism at re-
versed bending is basically the same as
ARCHIV F(!R DAS EISENHUTTENWESEN, GERMANY that of tensile loading. At stress levels
Vol 28, No.5/6 pp 3H-316, May-June 1957 above endurance limit the yielding of
Tension-compression fatigue tests on un- single crystals starts after a few thou-
notched and notched specimens from ferritic sand cycles, simultaneously at many places
steel 24 Cr Mo V 5.5 and austenitic steel at the highest loaded section of the spec-
X8 Cr Ni Mo Nb 15 at room temperature and imen. At stresses slightly below and near
at temperatures in the range of 500°C to the endurance limit, the slip lines occur
700°C.

Cont'd Behavior of Heat Resistant, etc. ;Contfd The Influence of Crystal, etc.

For notched specimens having K^ * 4.2, only in localized areas. Investiga-

the fatigue notch factor of the ferritic tions with electronic microscopes show
steel was about 2.7 at room temperature and that the submicroscopic cracks at the
1.5 at 500°C for long life. For the aus- surface of slip bands precede the micro-
tenitic steel, the fatigue notch factor and macro-cracks.
was about 1.3 at room temperature and
2.0 at temperatures in the range 550 to 22 figures, 17 references.
650°C. Comparison made with creep data
on same materials.
2 tables, 7 figures, 34 references.

HIJAB, W. A. HONEYCOMBE, R. W. K.
Statistical Appraisal of the Prot Some Observations of the Fatigue of
Method for Determination of Fatigue Silver Chloride
Endurance Limit
JOURNAL OF APPLIED MECHANICS, VOL 24, PROCEEDINGS OF ROYAL SOCIETY, SERIES A
pp.214-218, June 1957 No. 1229, October 1957

-?7-
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HMPEL, MAX, ALBERT KOCHENDOERFER AND HENDRICKSON, N. E,
EMIL'HILLNHAGEN
Special Techniques for Increasing Strength
The Influence of Crystal-Orientation on and Fatigue Life of Steel Stressed in
Fatigue Strength (At Stress Reversals) Torsion
of -Iron Single Crystals AS1M BULLETIN, No. 224, PP 40-42, Sept 1957
ARCHIV FflR DAS EISENHUTTENWESEN, VOL 28
No. 7, pp 417-422, July 1957 The application of shot-peening and pre-
stressing to torsion bar springs of A8660
Bending fatigue tests were made on electro- steel for track-type vehicles is discussed.
polished plate-like specimens of OC -iron. Details of the manufacture (machining, heat
Some specimens were wingle crystals, others treating) are presented. After shot-peen-
bi- and tri-crystals and poly-crystals. For ing, the bar is pre-set by twisting repeated-
each of the single crystals, their crystal- ly through 75 degrees until no further set
lographic oorientation was determined by occurs. Check fatigue tests are carried
sContfd TThe Influence of Crystal, etc. gContfd Special Techniques for Increasing,etc
• X-Ray technique. The results indicated that
crystallographic orientation of the single out by repeated twisting from 5 to 49
crystals was not a factor as indicated by degrees for at least 50,000 cycles. Of
a conventional S-N plot* The fatigue strength 38 bars tested, all met the ordnance re-
of the single crystals was about 13,500 psi; quirement of 5 degrees maximum set after
that of the poly-crystal was 17,800 psi. 50,000 cycles.
The former is about equal to the 002 per
cent offset yield strength; the latter is Individual results are given showing the
about 18 per cent less than the 0.2 per separate effects of shot-peening and pre-
cent offset yield strength of the poly-crys- setting, and the desirability of shot-
^tal. Orientation of grain boundaries was peening before presetting.
found to be a significant variable.
4 tables, 7 figures, 19 references.

HEMPEL, M., AND A. SCHRADER HERZOG, A.

Slip Lines at the Surface of Pure Aluminum Fatigue Testing of Turbine Buckets
Specimens Loaded in Reversed Bending
ARCHIV Fife DAS EISENHfeTENWESEN, VOL 28, PROCEEDINGS, SOC. FOR EXPERIMENTAL
No. 9, pp 547-556, September 1957 STRESS ANALYSIS, VOL XV, No. 1
pp 21-34, 1957
Flat specimens of pure poly-crystalic al-
uminum with 99.9$ Al were tested. After Special equipment is described for fatigue
fabricating, the specimens were heated for tests on turbine buckets under simulated
1/2 hour at 350 C-and air cooled, There- service conditions. A static tension load
• after, the flat surfaces were polished is applied directly, bending is induced by
electrolytically. It was found that the lateral vibration at 150 cps (the natural
endurance limit (about 1.5 kg/mm ) of pure frequency of the bucket system), and the
•aluminum for all practical purposes, required temperature distribution is ob-

s Contfd Slip Lines at the Surface, etc. sCont'd Fatigue Testing of Turbine Buckets
coincides with its static yield strength. tained by induction heating.
The fatigue loaded aluminum specimens show Stresses are obtained from strain gauge
a considerable workhardening with increased readings at room temperature combined
loads and with lifetime. with deflection readings at elevated
Slip lines occur in the crystal surfaces temperature. Results are presented for
or in the grain boundaries and their number S-816 and Haynes Stellite 21 buckets at
and extent also increase with increasing 1350°F and 1500°F.
loads and lifetime« At smaller loads the
slip lines occur later, and some lines can
be detected (on a few crystals) at loads
considerable below endurance limit. At
loads of the magnitude of 38 to 45/6 of endur-
anceCopyright
limitby ASTM
no slipInt'l (all lines could
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HESS, ROBERT., ROBERT W. FRALIGHT AND HEYWDOD, R. B.
HARVEY H. HUBBARD The Effect of High Loads on Fatigue
Studies of Structural Failure Due to (in Aluminum Alloys)
Acoustic Loading
PROCEEDINGS, COLLOQUIUM ON FATIGUE
NACA TN 4050, July 1957 STOCKHOIM, SWEDEN, MAY 1955, PP 92-102
METALLURGICAL ABSTRACTS, ENGLAND 24,
Some discussion of the acoustic fatigue Part 8, p. 619, April 1957
problem of aircraft structures is given
along with data pertaining to the acoustic Heywood reports fatigue tests on aluminum
inputs from some powerplants in common use. alloys, and the effect of a single pre-
Comparisons are given for results of some load, a batch of high pre-loads, and
fatigue tests of flat panels and cantilever periodic high loads. Occasional tensile

sCont'd Studies of Structural Failure, etc,

sCont8d The Effect of High Loads, etc.
beams exposed to both random and discrete-
type inputs. In this regard it appears loads in excess of half the P.S. improve
that both the stress level of the test the fatigue life; compressive loads cause
and the type of model are significant! a large reduction in life5 for this type
hence, no generalization can be made at of loading the cumulative-damage rule is
this time. With regard to increasing the entirely unsatisfactory. For tensile
fatigue life, it was noted that increased loads of given magnitude, the improvement
stiffening of a panel due to curvature and with periodic overloading is greater than
pressure differential is particularly with 10 pre-loads, and a single pre-load
beneficial. produces least improvement; the beneficial
effect is less when the fatigue stresses
are high.The larger positive gusts encount-
ered by aircraft should considerably in-

HEYWOOD, R. B. gCont*d The Effect of High Loads, etc.

Simplified Bolted Joints for High Fatigue crease their life. Compressive stresses
Strength, Tight Clamping, Close Pitch, due to landing may drastically reduce
and Stress-Relieving Grooves aircraft life. The beneficial effect
of a tensile load is lost if immediately
ENGINEERING, BRITISH, VOL 183 followed by a small compressive loade
pp 174-178, February 8, 1957 Periodic overloading applied once every
105 - io~~° miles of an aircraft's life
In this article, which is concerned with should increase its life.
bolted joints for aircraft structural
members, two extreme designs of joints
are compared—one in which the proportions
are carefully chosen so that the nominal

ContfdD Simplified Bolted Joints, etc. HOOPER, RoCo

stresses in sections are uniform, and Molding-Finish Interactions in Fatigue
the other of unorthodox design of the of Glass Reinforced Polyester Resins.
shortest possible length in which no
taper is given to the individual members. PLASTICS TECHNOLOGY, V. 3, PP 644-649
The short joint, with close-pitched August 1957
bolts clamped tight and with a stress-
relieving groove, is shown to be superior Investigation of the effect of various
in fatigue. finishes and euie cycle speeds on laminate
properties.
-29-
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HORGER, 0. J. AHD H. R. NEIFERT HUNTER, M. S. AND W. G. FRICKE, J£.
Fretting Corrosion of Large Shafts as In- Cracking of Notch Fatigue Specimens
fluenced by Surface Treatments ASTM PREPRINT, ANNUAL MEETING 1957
ASTM PREPRINT, ANNUAL MEETING 1957 Observations were made of the initiation
Rotating bending fatigue tests were carried and propagation of fatigue cracks in
out on 7-9/16 in.diameter shaft forgings of notched 6061-T6 aluminum alloy specimens,
0.5C steel (90/100,000 psi UTS) in the tested in Ro R« Moor ma chine s» The theor-
Timken testing machine. A disk was press- etical stress concentration factors for
fitted on one end of the forging, and the the circumferential notches varied from
disk seat was either chrome-plated (.010 in. 1 to 18<,9<. A plastic replica technique
thick) or treated by phosphate coating. was used for examining and recording the
Limited testing indicated appreciable fatigue cracks.

;Contfd Fretting Corrosion of Large, etc. sCont'd Cracking of Notch Fatigue, etc.
improvement with chrome plating, and little Results showed that the theoretical stress
if any with phosphate coating. Similar at the notch root was the main factor con-
tests were made on model tailshaft assemblies trolling fatigue crack initiation and the
of Oo25C steel (55/60,000 UTS), having a early stages of crack propagation,. Cracks
welded inlay deposited on the 5 3/4 in. formed at the notch when the theoretical
diameter propeller hub seat. The results stress exceeded a critical value, roughly
of two tests were in agreement with those equal to the endurance limit of smooth
previously obtained on non-welded shafts specimens0 However, cracks formed at stresses
of the same type of steel. below the notched endurance limit did not
Information is presented on the method of grow appreciably,. The halting of crack
'surface rolling of 27 in. diameter marine growth at a critical size between 0.1 and
propeller shafting to improve its fatigue 1.0 mm, previously reported for smooth spec-
resistance in the presence of fretting cor- imens was also observed with specimens hav-
rosion. ing the less severe notches.
HUGO, J.P. IU£, WALTER
Fatigue Tj"ests on Notched and Unnotched Sheet
Failure of Aluminum Alloy Fan Blades Specimens of 2024-T3 and 7075-T6 Aluminum
Alloys and of SAE 4130 Steel with Special
SOUTH AFRICAN MECHANICAL ENGINEER Consideration of the Life Range from 2 to
South Africa, 5, No. 9, pp 371-381, 10,000 cycles
April 1956 and
CORROSION, UNITED STATES 13, No. 10, NACA, UNITED STATES, T.N. No.3866, Dee.1956
page 149, October 1957. JOURNAL ROYAL AERONAUTICAL SOCIETY,
ENGLAND, 6l, No.557, page 370, May 1957
The notched specimens had theoretical
stress-concentration factors of 2<,0 and

tGontfd Fatigue Tests on Notched, etc.

HULT, J. A. H.
Fatigue Crack Propagation in Torsion 4.0 and the mean loads were 0 and 20 or
50 ksi» It was found that repeated ap-
JOURNAL MECHANICS AND PHYSICS OF SOLIDS plications of stresses in the vicinity
VOL 6, No. 1, pp 47-52, 1957 of the ultimate strength on notched and
unnotched specimens produced failures in
a much smaller number of cycles than
might be inferred from previously published
data. Ratios of fatigue strengths of un-
notched specimens to those of notched
specimens are given.
-30-
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HI£, WALTER AND ARTHUR J. MCEVILY, JR. IVANOVA, V.S AND I.A.ODING
Static Strength of Cross-Grain 7075-T6 Fatigue of Metals Under Contact Friction
Alluminum-Alloy Extruded Bar Containing (Russian) Ustalost* metallov pri kontakt-
Fatigue Cracks nom trenii
IZVJ5STIIA AKADMII NAUK SSSR, OTDELENIE
NACA,USA, TM 3394, April 1957 TEKHNICHESKIKH NAUK, No.l, pp 95-102
Cross-grain specimens of 7075-T6 aluminum- January 1957
alloy extrusion containing fatigue cracks of
various lengths were subjected to static Decrease in fatigue limit of Cr-Ni-Mo
tests to determine residual static strength. steel during contact friction is explained
Small cracks resulted in disproportionately as due to electroerosion from thermoelect-
large reductions of static strength. ric currents produced by changes in con-

iCont'd Static Strength of Cross-Grain, etc.

sCont'd Fatigue of Metals Under Contact,etc,
Comparison of the results with those for
the with-grain direction revealed no sig- tact resistance. This erosion leaves
nificant difference. However, it is vacancies in the crystal lattice. Fatigue
cautioned that cases may arise for 7075-T6 limit can be raised by changing the dir-
or for other materials where the cross- ection of the thermoelectric current
grain residual static strength is substanti- through proper choice of materials or
ally inferior. The effects of biaxLality by inducing a counter-current.
and ductility on notch sensitivity under
static loading are discussed in appendices.

ISHABASH, M. IWAMOTO, K.
Fatigue Rupture of Metals Study of Corrosion Fatigue; Method of
Measuring Damage Caused by Corrosion
JOURNAL JAPAN SOCIETY OF MECHANICAL Fatigue (Japanese)
ENGINEERS, VOL 60, pp 15-19, January 1957 JAPAN SOCIETI OF MECHANICAL ENGINEERS
TRANSACTIONS, VOL.23, PP 238-241,March 1957
A description of the tensile tests, slip
rupture, fatigue process and fretting Test-pieces corroded by water stream
corrosion of light alloys. under various rotating bending stresses;
then tested to failure in air at stress
about 2($ above fatigue strength.

IVANOVA, V.S.
JACQUET, Ao
Intergranular and Intragranular Nature
of the Destruction of Armco Iron Due to Micrographic Study of an Alpha Brass
Fatigue. (Russian) Mezhzerennyi i vnut- Subjected to Plane Alternated Bending
rizerennyi kharakter razrusheniia armko (Etude micrographique d"un laiton sounds
zheleza pri ustalosti a la flexion plane alternee)
DOKLADY AKADEMUNAUK SSSR, V 114, No.3 REV .METALLURGY, FRANCE 54,
PP 537-540, May 21, 1957 No. 7, pp.489-519, July 1957
With cyclic tensions exceeding the yield
limit, the intergranular plasticity does
not leave enough time for the granules to
become strengthened. The process of dif-
fusion
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JACQUESON, R. JAENICHEN, ERICH
Modifications of Crystalline Fixture Comparison Between the Processes of Wire
Produced by Alternating Stresses Patenting by Electric Resistance and by
PROCEEDINGS COLLOQUIUM ON FATIGUE, Heating in the Gas-Fired Continuous Furnace
STOCKHOLM, SWEDEN, in May 1955, pp.103-110 (German) Vergleich der electrischen Wider-
1956. METALLURGY ABSTRACTS, ENGLAND 24, standspatentierung mit der Bleipatentierung
Part 8, page 643, April 1957 nach Erhitzen im gasbeheizten Durchaiehofen
STAHL UND EISEN, V.77, No.25, pp 1802-1817
Jacqueson measured small distortions of December 12, 1957
the crystal lattice of a single crystal
of pure aluminum by using it to focus Effects of wire heating temperature, lead
X-Rays, the size of the focal spot measur- bath temperature, and heating rate in el-
ing the angle of distortion.

sContfd Modifications of Crystalline, etc. •nont*d Comparison Between the Processes,et<

A crystal, originally showing a distortion of
3; gave greater distortion when loaded to ectric resistance patenting on the prop-
400 g/mm2 and recovered to 1 on resting; erties of steels containing 0.35 to 0.95$
a subsequent loading of 700 g/mm produced C. Testing wires with the spring, twist-
no distortion; this experiment probably ing, and bending fatigue tests; behavior
illustrates the mechanism of under-stressing. in aging.
At higher temperatures e.g. for aluminum at
250°C., the recovery process that is re-
leased by a light deformation is associated
with fecrystallization.The theory of this
effect is discussed thermodynamically.

JOHNSON, DONALD F. JENSEN, R.S.

Investigation of Some Mechanical Properties Fifteenth Progress Report of the Rolling
of Thermenol Compressor Blades Load Tests of Joint Bars
U.S. NATIONAL ADVISORY COMHITTEE FOR AEEA BULLETIN, VOL.58, No.535
AERONAUTICS.TECHNICAL NOTE 4097, 14 p. pp 1005-1025, 1957
(TL570 Un3t) October 1957
Reports progress on an investigation of
A comparison of AISI type 403 stainless design features on simulated service be-
steel and thermenol blades. Modulus of havior of steel joint bars for railroad
elasticity and rigidity and damping were rails. Tests consisted of rail wheel
slightly lower for thermenol. However, rolling rectilinearly over rail joint*
thermenol showed better resistance to Forged and cast steel joint bars investi-

'Confd Fifteenth Progress Report, etc.

sContfd iInvestigation of Some Mechanical,etc,
gated. Differences in fatigue lifetimes
corrosion by sea water and proved equal and scatter attributed to porosity, hard-
or superior to stainless-steel in fatigue ness differences, and surface conditions.
strength. Bending-fatigue tests also run on T-sec-
tion specimens sectioned from joint bars0
Results show increased fatigue strength
with increase in hardness. Also specimens
with machined and ground surfaces had
fatigue strengths in the range 50 to 100
per cent higher than those of specimens
with as-rolled surfaces.
-32-
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KAMMEKER; A. KEMSLEY, DoS.
A Theoretical Definition of Fatigue limit The Behavior of Cold-Worked
PROCEEDINGS COLLOQUIUM ON FATIGUE, Copper in Fatigue
STOCKHOUi, SWEDEN, in May 1955, PP 123-130
1956, METALLURGY ABSTRACTS, ENGLAND 24, aeronautics
Part 8, pp 614-615, April 1957 aust

A mathematical treatment of the relation

between the endurance limit and the elastic
limit for isotropic homogeneous solids.

sContsd A Theoretical Definition of Fatigue

KMSLEY, D«S.

The results are not applicable to metals, The Behavior of Fractured Copper
which have fatigue limits much lower than Fatigue Specimens on Annealing
are calculated from the theory; two reasons
for this divergence are that the elastic INSTITUTE OF METALS JOURNAL,
limit for metals depends on the rate of V 85, pp 417-420 + 2 plates
application of the load, and during fat- May 1957
igue tests there is liberation of heat by
internal friction, an effect that is ig-
nored in the theory.

KAWADA,, Y. AND H0 NAKAZAWA KEMSLEY, Do So

On the Fatigue Limit of Steel Specimens Crack Paths in Fatigued Copper
with Cold-Rolled V-Notch
JOURNAL INSTITUTE OF METALS, VOL 85
TRANSACTIONS JAPAN SOCIETY OF MECHANICAL pp 420-421, May 1957
ENGINEERS, VOL 23, pp 190-193, March 1957
A study of transcrystalline and inter-
crystalline fatigue cracks on rotating
cantilever fatigue specimens of high-
conductivity copper (99.95^ Cu.)

KEMSLEY, Do S. KENNEDY, A. J.
The Nature of Persistent Slips Bands A New Detection of Fatigue Damage
in Fatigued Copper in Metals
PHILOSOPHICAL MAGAZINE, VOL 2, Series 8, NATURE, VOL 179, PP 1291-1292
pp 131-132, January 1957 June 22, 1957
Evidence of the nature of persistent slip Creep characteristics of lead wire
bands obtained during metallographic work change at 60-80# of fatigue life.
on rotating cantilever fatigue specimens
of annealed high-conductivity copper.
23-
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KENNEDY, A. J. KESSLER, H., AND H. L. WINTERSTEIN,
Problems of Combined Creep and Fatigue Danger of Over-Development in Hypereut-
Design ectic Aluminum-Silicon Alloys
ENGINEER, VOL 204, PP 444-447, LIGHT METALS, pp 387-388,December 1957
September 27, 1957 Discusses increasing tendency to use
Reviews the evidence relating to interaction these alloys* Hardness, strength at
between the two processes of deformation elevated temperatures, and anti-friction
and fatigue, particular attention being properties improved^ but homogeneity is
given to the case where the deformation diminished, favoring local weaknesses
occurs by creep. that may be particularly harmful to
fatigue strength.

KENNEDY, A. J. KICHIRO, B., H. HUJI, AND S. CMORI

Corrosion Fatigue of Steel Wire
Effect of Fatigue Stresses on the Recovery
Properties of Metals (Lead)
JAPANESE SOCIETY OF MECHANICAL ENGINEERS
NATURE, ENGLAND 178, No. 4537 TRANSACTIONS, VOL 23, pp 484-488
pp 810-811, 1956 July 1957
JOURNAL INSTITUTE OF METALS, ENGLAND 85,
Part 7, page 550, March 1957

KEPPERT, J. L., C. A. PATCHING, M. R. RICE KLAASSEN, W. AND A. HARTMAN

AND J. S. ROBERTSON
The Fatigue Diagram for Fluctuating
Fatigue Characteristics of a Riveted 24S-T Tension of Single-Lap Joints of Clad
Aluminum Alloy Wing. Part 3 Test Results. 24S-T and 75S-T Aluminum Alloy with
two rows of 17S Rivets,
COMMONWEALTH OF AUSTRALIA, AERONAUTICAL
RESEARCH LABORATORIES, REPORT ARVSM 243, NATIONALS LUCHTVAARTLAB, AMSTERDAM,
October 1957 REP. HOLLAND, No. M 1980, 4 pages, 1955
METALLURGY ABSTRACTS, ENGLAND 24
Fatigue tests were conducted on 178 speci- Part 8, pp 619-620, April 1957
mens from 90 P-51 Mustang wings. Tabulation

:Cont'd Fatigue Characteristics, etc. KOOISTRA, L.F.

of fatigue life, type of failure and Effect of Plastic Fatigue on Pressure-
load of range for each specimen. Crack Vessel Materials and Design
propagation rate, local strain distribu-
tion, types of fatigue failure, effect WELDING JOURNAL, V. 36, pp 120s-130s
of preload and variation in structural March 1957
flexibility.
Establishes the parameters with respect
to the plastic fatigue characteristics
of pressure-vessel materials.
34

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KOSTENKO, D,I. KRISHNAN, A.A. AND K. D. MAJI,
Effect of Macrostructure and Surface Condition Fatigue Failure - A Structure Study
of Steel Dies on the Formation of Thermal JOURNAL OF SCIENTIFIC & INDUSTRIAL
Fatigue Cracks. (Russian) Vliianie makros- RESEARCH, V l6B, pp 105-116, March 1957
truktury stali i sostoianiia poverkhnosti
shtampov na Obrazovanie v nikh treshchin Appreciable change in structure involving
termicheskoi ustalosti. alteration in shape of grains with the
AVTOMOBIL'NAIA I TRAKTORNAIA PRdfYSHLENNOST» partial formation of crystallites having
No. 8, pp 29-34, August 1957 random orientation takes place both above
and below the endurance limit in Cu0
It was found that surface deterioration
of dies occurs soonest in dies which have
less dense structure and whose surface

sCont'd Effect of Macrostructure, etc. KUDRIAVTSEV, I*V<»

Possible Simplification of Sample Shape
fineness is low. Of the specimens tested, for Fatigue Testing of Metals. (Russian)
poorer behavior was exhibited by the car- Vozmozhnye Uproshcheniia formy Obraztsov
burized samples than those machined with Dlia ispytaniia Metallov na Ustalost!.
cutting tools and polished; best of all
were those hardened by shot peening. ZAVODSKAIA LABORATORIIA, V. 23,
pp 461-468, April 1957
Several examples of fatigue testing of
metals are described, using round samples
on Shenk and UIFM-20 machines and flat
samples on resonance machines. Shows the
possibility of significant simplification

KOUDRIAVTZEV, I.V. AND N. M. SAVINOVA • Cont'd p oPossible Simplification, etc.

peening of i
as a of shape of steel samples by surface
working the sections gripped in the
f clamps. The use of this working makes
the thickening of the grip ends unnec-
SVAR SBORNIK, USSR 2, Nos. 1/2, pp 127-139 essary and permits fatigue investigation
1953, AND BIBLIOGRAPHICAL BULLETIN FOR of samples with uniform cross sections.
WELDING, FRANCE 9, No. 4/6, page 158E, Cold working can be achieved by rolling,
April-June 1957. shot peening, or coining.

KRAUSE, G. AND B. WINTER KUDRIAVTSEV, I.V*, AND L.M. ROSENMAN

Further Investigations of the Strength Relieving Residual Stresses From Cold
of Bonded Metal Joints Worked Bars by Means of Axial Strain.
METALLOVENDENIE I OBRABOTKA METALLOV,
ALUMINUM, p. 669, October 1957 No. 7, PP 7-13, July 1957
Authors review work of others and des- Samples were passed through a fixture
cribe their studies with metal adhesives. with three rolls to produce surface stresses,
Bond strengths measured for various sur- then subjected to various fatigue tests.
face states, different corrosive environ- It is possible to conserve a part of the
ments and at various temperatures. Studied residual loading by means of axial load-
thickness of adhesive film; and tensile, ing.
shear and shear fatigue strengths. Include -35-
tests
C with
o bonding
p y rresins.
ig AhST t
M Intb
'
l y (all
Dow nlo a ded/printed by
University o f W ash ington (Univ
KUHN, Po k
Effect of Geometric Size on Notch Fatigue Thermal Fatigue of Metals (Russian)
PROCEEDINGS, COLLOQUIUM ON FATIGUE, 0 Termicheskoi Ustalosti metallov
STOCKHOIM, SWEDEN, in May 1955, PP 131-139,
1957. METALLURGY ABSTRACTS, ENGLAND 24, TBPLOENERGETIKA, ? 4, No. 12
Part 8, page 615, April 1957 PP 32-35* December 1957
For the effective stress-concentration factor Comparison of thermal fatigue of steel
Kj*,K.uses the Neuber formula;K«= 1 + (K™ - l)/ tubes during radial heat flow in tension-
1 + TA~l/2/(T-<0)r 1/2, where 1^ is the compression testSo
factor obtained by the theory of elasticity,
r and 10 are the root radius and the flank

sCont'd Effect of Geometric Size, etc. LASSITER, TRST.TF; w0,ROBERTw.HESS,AND

HARVEY Ho HUBBARD
angle of the notch, respectively, and A An Experimental Study of the Response of
is a materials constant. Tests are re- Simple Panels to Intense Acoustic Loading.
ported on Aluminum alloys, $>r which A » 0,02 in
there was no difference between unpolished JOURNAL OF THE AFRONAUTICAL SCIENCES
and electropolished sheet specimens. VOL 24, January 1957

KUHN, P< LAURENT, Po

Recent Investigations on Fatigue at
The Effect of Size on the Fatigue of 1'Institut de Recherches Metallurgiques
Notched Specimens (Influence des dimensions de Saarebruck
sur la fatigue des pieces entaillees). PROCEEDINGS COLLOQUIUM ON FATIGUE,
STOCKHOIM, SWEDEN, in May 1955, PP 141-147,
REV. ALUMINUM, FRANCE, 34 No. 246 1957o METALLURGY ABSTRACTS, ENGLAND 24,
Page 794, September 1957 Part 8, page 6l6, April 1957
H. Buhler and W, Schreiber made fatigue
tests on steels and aluminum alloysj
resting a Ni-Cr steel during a test did
not prolong its life 5 understressing in-

KUHN, PAUL , AND ROGER W. PETERS

sCont'd Recent Investigations on Fatigue, etc
Some Aspects of Fail-Safe Design of
Pressurized Fuselages
NACA TN 4011, June 1957 creased the life of an Al-Mn alloy.
H. Hendus and Ge Kraus studied the
Separate investigations have dealt with the fatigue limit of Armco iron0 P« Laurent
critical crack length of flat sheets or of and A Kovacs applied magnetic measurement
unstiffened cylinders and with the type or to fatigue studies.
rupture experienced by stiffened cylinders.
These investigations are correlated, supple-
mented by new tests, and combined into a
uniform scheme for predicting critical crack
length and type of rupture in stiffened pres-
surized cylinders. ^6-
Cop yrig h t b y A ST M
Dow nlo a d ed/printed by
Unive rsity o f W ash in
LAtix, R;J. IAZAN, B. Jo
Component Fatigue Analysis for Maintenance Fatigue Under Hesonant Vibrations Con-
sidering Both Material and Slip Damping
MECHANICAL ENGINEERING, pp 656-658,
July 1957. PROCEEDINGS, SOCIETY FOR EXPERIMENTAL
STEESS ANALYSIS, VOL XV, No. I,
Discusses problems of fatigue failures pp 1-20, 1957
of fasteners and other highly stressed The general nature of material (internal)
parts. and slip (external) damping is analyzed,
and the significant parameters determined.
Both can contribute to reduce effectively

sCont'd Fatigue Under Resonant Vibrations,etc

. LAVERY, J. H., W. A. MAPP,AND W. S. GOATES
the high fatigue stresses associated with
Fatigue Testing of Butt Welds resonant operation. Important parameters
include stress range and distribution for
AUSTRALASIAN ENGINEER, AUSTRALIA 49, material damping9 and contact geometry and
No. 5, pp 66-68, May 7, 1957 interface pressure for slip damping. Ap-
proximate methods are now available to
compute their respective magnitudes. In
many cases^ material damping predominates
at high stress, whereas under optimum
pressure slip damping predominates at low
stress-

LAZAN, B. J. et al LAZfiR* LoS.

Properties of Materials and Parts Under Accelerated Fatigue of Plastics

Alternating Force ASTM BULLETIN Noo 220, pp 67-72
February 1957
STATUS REPORTS OF UNIV. OF MINNESOTA FOR
AF CONTRACT AF-33(6l6)-2803; The Prot progressive loading method was
STATUS REPORT 57-1, 28 Feb 1957; 57-2, 30 Apr examined with regard to its suitability
1957; 57-3, 30 June 19575 57-4, 31 Aug 19575 for testing plastics. Tests were made
57-5, 31 Oct 1957. in a Moore type machine, with lead shot
loading, and in a modified Sonntag SF-10U
machine, on three plastic materials,
acrylic, polystyrene and nylon.

LEGHORN, GEORGE sCont'd Accelerated Fatigue in Plastics

The Story of Shot Peening Results for the Prot method were plotted
as failure stress v the square root of
AMERICAN SOCIETY OF NAVAL ENGINEERS the rate of loading, and the best-fitting
JOURNAL, V 69, pp 653-666, Nov 1957. straight lines were drawn. The estimated
endurance limits, obtained by extrapola-
Machines for shot peening; types of tion, were generally higher by 17 to 40#
shot used; shot peening to specifica- than those given by the standard Wohler
tions; fatigue failures; uses of shot method. The exception was nylon which
peening; variables. gave a value lower by 8# under axial cy-
clic stress.
-37-
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LE GRAND, R., AND R. ESQUERRE IEVY, JOHN C.
Some Results of Fatigue Tests Carried Oat Cumulative Damage in Fatigue - A Design
on Aluminum Alloys by the Application of Method Based on the S-N Curve
Tensile-Compressive Stresses {Quelques JOURNAL ROYAL AERONAUTICAL SOCIETY,
resultant d'essais de fatigue 1en traction- ENGLAND 61, No. 559, pp 485-491,July 1957
compression sur des alii ages d aluminum)
It is suggested that a convenient way of
REV. METALLURGY, JEANCB 54, No. n presenting the results of fatigue tests in
pp 840-854, November 1957 which two different stress amplitudes are
applied alternately is to plot log N against
Fatigue resistance of aluminum alloys of the log (nx/n) where N is the total cycles to
243 and 75^ type was studied and comparisons failure and (n^/n) is the fraction of cycles
were made between results obtained with alloys run at the high stress. With these coordin-
gCont'd Cumulative Damage in Fatigue
sCont'd Some Results of Fatigue Tests, etc,
ates a simple geometrical construction gives
of similar_ composition
..._,
. English ^but
gj
of different a safe design method for the two-stress
(French, and uU.S) origin. The level system using only the conventional S-N
preparation of specimens and the experi- curve, and the value of (n,/n) expected to
mental procedure are described in detail. be encountered in service.
The findings are tabulated and special The conclusion is checked against a wide
attention is given to the angle effect and range of experimental results taken from
to the fatigue behavior of Alclad material. six different sources in the literature
Testing equipment installed at the Toulouse covering rotating-bending and push-pull
(France) laboratories of the Aeronautical testss ferrous and non-ferrous metals, any
Technical Services where the research work order of stressing and length of programme
described was carried out, is described cycle from 50 up to 5 million.
and pictured.

LEIBOVIC, K.N. LEVY, JaCo

Strain-Aging as an Explanation of the
Fatigue of Metals "Knee" in the Fatigue Curve of Mild Steel
INDUSTRIAL CHmSTRY, VOL 33, METALLURGIA, VOL 56, No. 334, PP 71-73
pp 194-195, April 1957 August 1957
Discusses some aspects of metal fatigue The strain-aging effects for mild steel
of interest to phemical engineers, par- are briefly discussed. Two S-N curves of
ticularly on the design and use of gradually decreasing slope are then assumed
structures and machines. for non-strain-aged and for fully strain-aged
material respectively. It is suggested
that strain-aging strengthens a certain

gCont'd Strain-Aging as an Explanation, etc,

LEVY, JOHN C.
proportion of "damaged-nuclei1, and at a
Discussion. Speed Effect in Fatigue certain stress level this proportion
reaches 100$. On this basis, by transforma-
PROCEEDINGS OF ROYAL SOCIETY, SERIES A tion from one curve to the other, an inter-
No. 1229, October 1957 mediate curve with a sharp fkneef typical
of mild steel is derived, The effect of
higher temperatures which increase the
diffusion rate of carbon and nitrogen atoms,
moves the 'knee* upward and to the left.

-38-
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 LINGER J.R. LISSNER, Do
The Detection of Fatigue Cracks in New Results on the Importance of the
Specimens Under Dynamic Loading Surface Effect in the Initiation of
Fatigue Cracks (Swedish)
AIRCRAFT ENGINEERING, VOL XXIV, No.345 JERNKONTORBTS ANNALER, VOL 141, 1957
November 1957 Fatigue experiments on a quenched and tem-
The manufacture of a new form of electrical pered chromitim-nickel-molybdenum steel con-
firmed the existence of a surface effect
tape permits further investigation of a which contributes to the initiation of
method of fatigue crack detection first fatigue cracks« By 9 times repeated turn-
suggested by Henry W. Foster (Ref«,2).The ing of a thin surface layer the life of a
method is applicable to light alloys and fatigue test piece was increased 633 per
normalized steels. When a crack crosses cent.

gCont*d The Detection of Fatigue Cracks,etc. LISSNER, 0,

the wire it breaks it in a static manner; a
relay, and in turn some warning device, is Investigations on the Processes Occurring
actuated by the interrupted circuit, in the Surface Layer of Fatigue Specimens
The final results suggest that the types of
fatigue crack detector considered form a PROCEEDINGS COLLOQUIUM ON FATIGUE,
suitable means by which to give warning of STOCKHOLM, SWEDEN, in May 1955,
the impending failure in aircraft components PP 14B-15S, 1956
and structures under laboratory or flight METALLURGY ABSTRACTS, ENGLAND 24
conditions up to about N = 10 x 10° cycles. Part 8, page 615, April 1957
6 references, 14 diagrams, 13 photographs

LIPSITT, H.A., AND G.T.HORNE LIU, Ho Wo, Ho To CORTEN, AND G. M. SINCLAIR

The Fatigue Behavior of Decarburized Steel Fretting Fatigue Strength of Titanium
Alloy HC130B
ASTM PREPRINT, ANNUAL MEETING 1957
ASTM PREPRINT #66, ANNUAL MEETING 1957
Reversed axial loading tests were made on
samples of SAE1008 steel in the as-rolled and Plane bending fatigue tests were carried
in the decarburized condition, and R. R. Moore out on rectangular specimens of RC130B in
fatigue tests were made on samples in the Krouse plate fatigue machines to study the
latter condition only* The partial removal effect of a number of variables on the
»of carbon and nitrogen resulted in a reduc- fretting fatigue strengthe Fretting was
tion in life at a given stress and a1 lower- produced by gripping one end of the test
ing of the fatigue limit, the 'knee of the piece between two pads, and vibrating the
US/N curve occurring at a longer life. other end.

sCont'd The Fatigue Behavior of Decarburized,et Cont'd Fretting Fatigue Strength , etc.
The results suggest that complete removal The results showed that pads of hardness
would suppress the fatigue limit to life- below a critical range (100 to 230 DPH)
times beyond practicable tests - approach- produced the smallest decrease in fatigue
ing non-ferrous metals behavior. strength (less than 2050. Pads of high
hardness reduced the fatigue strength 60
The authors put forward an explanation of to 80#0 Gripping pressures above 4000 psi
their results based on the strengthening had little additional effect. Oxidizing
effect of strain aging in plastically de- treatments, a teflon coating, and shot
formed steel. peening were each beneficial to some ex-
tent. Tungsten carbide plating, aluminiz-
ing and the exclusion of oxygen resulted
-39- in no improvement.
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 LOCAEE, X. MC GAMMON, R. D.s AND H.M.ROSENBERG
Bending-Fatigue Tests with Superimposed The Fatigue and Ultimate Tensile Strengths
Frequencies of Metals Between 4.2 and 2390k.
PROCEEDINGS, COLLOQUIUM ON FATIGUE, PROCEEDINGS ROYAL SOCIETY, V 242, Ser A,
STOCKHOIM, SWEDEN, in May 1955, pp 160-168, pp 203-211, October 29, 1957
1956. METALLURGY ABSTRACTS, ENGLAND, 24,
Part 8, page 658, April 1957 Data on Cu,Ag,Au,Al,Mg, Zn, and Fe. Except
for Zn and Fe, which exhibit brittle frac-
An apparatus for producing non-sinusoidal ture at low temperatures, the fatigue char-
fatigue stresses Toy modulation of amplitude acteristics improve very considerably as
was previously described by Locati (Met. the temperature is reduced.
Italy, 44, page 135, 1952.) The apparatus

;Cont*d Bending-Fatigue Tests with, etc. MC CLINTOCK, F.A.

Variability in Fatigue Testings Sources
now described produces a different type and Effect on Notch Sensitivity
of irregular stressing by superimposing
two very different frequencies. Tests PROCEEDINGS, COLLOQUIUM ON FATIGUE,
are reported on Duralumin; with total STOCKHOIM, SWEDEN,in May 1955, PP 171-177,
stress-amplitudes of 22-32 kg/mm^, the 1956. METALLURGY ABSTRACTS, ENGLAND 24,
fatigue life was greatly shortened by Part 8, page 615, April 1957
replacing 10$6 of the L. F.(3 c/s) by A mathematical relation is deduced between
HoFo (42 c/s), and a further reduction the scatter of fatigue life and the position
of life occurred with up to 40# of H. F. of failure,, and a comparison is made with
stresses. experimental results. From a statistical
analysis taking into account the stress

LUNDBERG. BO, AND EGGWERTZ SIGGE iCont'd Variability in Fatigue Testing, etc,
The Relationship Between Load Spectra
and Fatigue Life
gradient of the surface, an estimate
THE AERONAUTICAL INSTITUTE OF SWEDEN, of notch sensitivity is obtained; data
REPORT No.67, March 1956 on an aluminum alloyiindicate that
AIRCRAFT ENGINEER, ENGLAND 29, No. 335, notch sensitivity is not due to statis-
pp 27-28, January 1957 tical effects alone.
A study of available data on accelerations
Experienced by fighter planes indicates
that the load spectrum for this category
can be approximated by a straight line in
.a semilog plot (Sa vs log.H).

'Cont'd The Relationship Between Load, etc. MARBLE, J. D. AND C. V. RUEHRWEIN

Two methods have been developed for the
correction or evaluation of fatigue life Barrel Finishing Operation Improves
times obtained by use of cumulative damage Fatigue Strength of Jet Engine Parts
theory or programme testing. TOOL ENGINEER, V 39, PP 99-101, Nov. 1957
In view of the results obtained, an adoption
of straight line spectra for programme test- Barrel finishing produced satisfactory
ing would yield 'programme test properties' finishes at acceptable rates of speed
or 'spectrum properties1, for materials or and relatively low costo Tests estab-
components, which would be of about the same lished that the degree of surface rough-
basic nature as S-N properties. ness has a pronounced effect on the
fatigue limits of hardened AISI 413©
-40- steel»
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 MICHEL, Ro
MA&IN, JOSEPH
A Quarter Century of Propulsion Shafting
Significance of Material Properties in Design Practice and Operating Experience
Design for Fatigue Loading II in the U0 S0 Navy
ASTM PREPRINT, ANNUAL MEETING 1957
MACHINE DESIGN, V 29, pp 95-99, Feb. 7, 1957
The progress in marine shafting design
A review of generalized failure theories with reference to methods of stress com-
and design recommendations for static putation and resistance to fatigue is re-
stresses and static stress concentrations. viewed o Examples of failures due to
torsional vibration, corrosion and fret-
ting corrosion are presented,. Stress
raisers at keyways and fillets have been

sCont'd A Quarter Century of Propulsion,etc,

MARIN, JOSEPH
reduced, and cathodic protection systems
Significance of Material Properties in installed. Cold-rolling of shafte is being
Design for Fatigue Loading III used to increase fatigue strength and im-
prove resistance to fretting corrosion.
MACHINE DESIGN, V 29, pp 124-134, Feb.21,1957 Simulated service fatigue tests on a small
scale have shown an improvement of nearly
A review of strength considerations in the 200# for a surface-rolled steel shaft in
design of members subjected to both simple a mangane se-bronze sleeve.
and combined fatigue stresses. In current design, the maximum shear theory
of failure is used, allowance is made
for off-center thrust and high speed turn
effects, and critical frequencies are a-
voided.

MARTIN, Z.G. MICHEL, R.

Fatigue in Automotive Parts (Spanish) Influence of Operating Experience and
Full-Scale Tests on Propulsion Shafting
CTEJCIA I TECNICA DE LA SOmDURA,V 7 Design of U0 S. Navy Ships.
November-December 1957
Role of part design, choice of metal, ASTM STP 216, page 107, 1957
heat treatment and coatings in reducing
fatigue tendencies. Fatigue in crank- Paper presented at a symposium on large
• shafts, bolts, pins, springs and gears. fatigue-testing machines at the ASTM's
60th Annual Meeting.

MARTIN, Z. GARCIA MORROGH, H.

Fatigue and Design in Welded Naval Con- Fatigue of Cast Iron
struction (Spanish)
CIENCIA Y TECNICA DE LA SOLDHDURA,V 7 FOUNDRY TRADE JOURNAL, V 102,
18 p, May-June, 1957. pp 239-244, February 21, 1957
Fatigue tests. Relationship between the Effect of surface rolling on fatigue
mechanical properties and their fatigue properties of both nodular and flake-
resistance. Admissible tension and safety graphite irons. Effects of elevated
factor. Role of structure shape. Riveted and low temperatures, surface finish,
and welded structures and fatigue stress. and annealing.

-41-
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 MQLLER5 FL, AND M. HEMPEL MORRISON* J.L*, Bo CRQSSIAND, AND§J.S.CoFERRY
Contribution to Evaluating Weld Defects Fatigue Under Triaxial Stress
of Welded Specimens from X-Ray Pictures ENGINEERING, BRITISH, VOL 183,
and Tension-Tension Fatigue Tests pp 428-431* April 5, 1957
ARCHIV rfb DAS EISENHOTraNWESEN, VOL 28,
No. 9, pp 531-541, September 1957 The authors have built a fatigue machine
for subjecting a thick-walled cylindrical
Tension-tension fatigue tests were performed specimen to repeated internal pressure.
on welded specimens of boiler steels having The state of stress in such a cylinder
an ultimate tensile strength of 44-65 Kg/mm^. can be regarded as a uniform triaxial ten-
The steel thicknesses ranged from 30 to 100mm, sion superimposed on a simple shear stress
According to the findings of X-Ray investi- which has a maximum value at the bore.
gations and ultrasonic methods, the specimens

sCont'd Contribution to Evaluating Weld,etc. sCont*d Fatigue Under Triaxial Stress

were divided in five groups and the follow- A number of preliminary tests have been
ing results were obtaineds(l) Defectless spec- conducted on this machine in which the bore
imens, the control groupi(2)specimens with of the specimen was protected by a thin rub-
bonding defects;(3) specimens with porosity ber film and the results compared with un-
and slag inclusions in the weld; (4) specimens protected specimens. The protected specimens
which were rewelded to correct some previous were superior to the unprotected specimens«
welding defects; (5)specimens with defectless As a result of the limited data available
welds but with defects (inclusions)in the on specimens tested in this machine, no
steel. exact interpretation of the results have
1 table, 9 figures, 13 references been made0

MORGAN, WILLIAM C, AND GEORGE C. DEUTSCH MORROW, JODEAN AND G0 M e SINCLAIR

Experimental Investigation of Cermet Turbine Fatigue Strength of Lapelloy as Influenced
Blades in an Axial-Flow Turbojet Engine. by Heat Treatment and Surface Finishing
U.S.NATIONAL ADVISOR! COMMITTEE FOR AERO- Methods
NAUTICS, TECHNICAL NOTE 4030, 20 pages DEPTo OF THEORETICAL AND APPLIED MECHANICS
(TL570Un3t) October 1957 REPORT Noo 540 (Sponsored by General El-
Chipping in the tip region was a common ectric Company, Aircraft Gas Turbine Div.,
characteristic in blade failures. Analysis Evendale Plant Lab,, Cincinnati 15, Ohio.
•indicates two probable causes of failure, Contract Code No0 46 22 60 334), Univ.
impact and fatigue,, Elimination of excessive of Illinois, April 1957.
A study was made of the fatigue and static
tensile properties of a modified 403 stain-

sCont^d Experimental Investigation, etc. gConfd Fatigue Strength of Lapelloy, etc.

less steel (designated as Lapelloy) as in-
fluenced by heat treatment hardness, re-
C in the combustion chambers and avoiding sidual stress^ surface roughness and various
conditions of extreme vibration chambers finishing methods„ It was found that at a
and avoiding conditions of extreme vibra- hardness of Rockwell C 30 the strength pro-
tion made an improvement in test blade life. perties were relatively insensitive to
residual stress and surface roughness0 Metal-
lographic examination of the heat treated
samples disclosed soft pools of delta fer-
rite in the matrix which may be responsible
for some loss of fatigue strength at high
-42- hardness*,
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MORROW, 'JODEAN, AND G. M. SINCLAIR HIROSHI NAKAMURA, SKERO UEDA, AND
TATSUO AMAKASU
An Analysis of Cyclic stress behavior for
A study of the Effects of Induction
conditions of Controlled strain Hardening on Fatigue strength (Japanese)
Report No. 543 of Dept of therorestical and JOURNAL OF RAILWAY ENGINEERING RESEARCH
APPLIED MECHANICS (Sponsored by General (Japan) V 14, PP 55-90, February 15, 1957
Electric Company, Aircraft Gas Turbine Div.,
Evendale Plant Lab., Cincinnati 15, Ohio. Numerous tests indicate that the increase
Contract Code No. 46 22 60 334), Univ. of in fatigue strength of a notched specimen
Illinois, August 1957. after induction hardening is due to com-
pressive residual stress existing on the
Time dependent relaxation of stress in metal surface and development of toughness in
which is held in a strained state is a well the material due to rapid heating and Goofinge

sContfd An Analysis of Cyclic Stress, etc. NEPPIRAS, E, Ac

known phenomenon. There also exists a cycle- Metal Fatigue at High Frequency
dependent relaxation of stress which occurs
under conditions of repeated straining. To PHYSICAL SOCIETY PROCEEDINGS, V 70, No044SB
investigate this type of behavior, the mean PP 393-401, April 1957
strain and amplitude of alternating strain Metal samples were subjected to tension-
is held constant in axial fatigue tests of compression stresses above the fatigue
SAE 4340, and the mean stress is measured limit at frequencies around IS kc per sec
as a function of the number of strain repet- produced by a resonant magnetostriction
itions . transducer. The fatigue limit was appre-
The practical significance of these findings ciably higher than that obtained from
is discussed, especially as relates to the L. F. measurements.
fading of residual stresses in machine parts
subjected to fatigue loading.

MOTT, NoF. NEWMAN, RoPo

A Discussion on Work-Hardening and Fatigue Influence of Weld Faults on Fatigue
in Metals Strength with Reference to Butt Joints
in Pipe Lines
PROCEEDINGS ROYAL SOCIETY, SERIES A,
ENGLAND 242, No. 1229, pp 145-227, Oct 29,1957 WELDING RESEARCH ABROAD, VOL. 35 pp 9-28
March 1957
In spite of much experimental work there
is still no satisfactory theory of fatigue. Testing was by alternate plane bending
This discussion was organized with the to develop stresses transverse to the
aim of collecting as many as possible of joint. It was found that the root zone
the relevant facts concerning work-hardening of welds, with and without backing rings,
in fatigue in metals.

;Cont'd Influence of Weld Faults, etc

MURRAY, J.D.

Steels at Elevated Temperatures exercised a predominant influence on

IRON AND STEEL, V 30, pp 493-495, October 1957 fatigue behavioro Except in the case
of lack of penetration, defects had
Corrosion resistance; fatigue; physical no significant effect on fatigue strength
properties; effects of deoxidation practice because of the over-riding influence of
and mechanical working on creep resistance* root zone.

-43-

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NIKISHOV, A.S., G. V. KURGANOV, AND NORLIN, PER V.
N. I. IARZHEMKSAIA
Designs of Welds for Close-Tolerance
The Effect of Thick Annodizing on the Metalworking Machines (Swedish)
Fatigue Strength of AK-4 and VD-17 Svetsade maskinkonstruktioner med sma
Aluminum Alloys (Russian) Vliianie glu- toleranser
bokogo anodirovaniia na ustalostnuiu
prochnost1 aliuminievykh splavov AK-4, SVETSAREN,, V0 22, No, 1, pp 11-22, 1957
and VD-17 Welded joint shrinkage. Fatigue strength.
Permissible stresses. Examples include a
METALLOVEDENIE I OBRABOTKA METALLOV, No. 12 hydraulic wallboard press and a 400 ton
pp 66-68, December 1957 ship-building press.
Study of the effect of anodic films.

NISHIHARA, T. and T. YAMADA NOVIK, A.Ao and Mo A. BALTER

Fatigue Life of Metallic Materials Under Rolling as an Efficient Method for Raising
the Wear Resistance of Pinions. (Russian)
Varying Repeated Stresses of Two Different Obkatka rolikami kak effektivnyi povysheniia
Stress Waves (Japanese) ustalostnoi prochnosti shesteren
TRANSACTION, JAPANESE SOCIETY OF MECHANICAL VBSTNIK MASHINOSTROENIIA, V 37, No. 10,
ENGINEERS, VOL 23, PP 136-141, March 1957 pp 65-68, October 1957.
As a result of the rolling process, resid-
Notched specimens of carbon steel and dural- ual strength develops on the metal surface.
umin tested and results were used to cal- This strength added algebraically to the
culate fatigue life. tensile strength produced in the working
process of parts, decreases the cyclic amp-
litude, and thus increases the life of parts.

NOREKARK, GLENN, E. and IAN D. EATON ODING, I.A,

Effect of Fatigue Crack on Static Strength Development of the Theory of Fatigue
2014-T6, 2024-T4, 6061-T6, 7075-T6, Open- of Metals (Russian) Razvitie teorii
Hole Monobloc Specimens ustalosti metalov
NACA Ttt 1428, May 1957 VESTNIK AKABEMII NAUK SSSR, V 27
Static tensile test results are presented pp 24-30, April 1957
for specimens of 2014-T6, 2024-T4, 6061-T6,
and 7075-T6 aluminum alloy containing fati- Historical survey of the theory of metal
gue cracks. The results are found to be in fatigue. Importance of the theory in
good agreement with the results reported present day industry.
for similar tests from other sources. The

;Cont«d Effect of Fatigue Crack, etc. OKAGAKI, N.

results indicate that the presence of a fatigs Relaxation Phenomena of the Fatigue
crack reduced the static strength, in all of Metals
cases, by an amount larger than the corres- INST. OF SCIENTIFIC AND INDUSTRIAL STUDIES,
ponding reduction in net area; the 6061-T6 al- OSAKA UNIVERSITY MEMOIRS, VOL 14
loy specimens were least susceptible to the PP 53-56, 1957
crack and the 7075-T6 alloy specimens most
susceptible. It is indicated that a 7075-T6 Structural changes during fatigue detected
specimen may develop as little as one-third by internal friction measurements.
of the expected static tensile strength when
the fatigue crack has consumed only one-
fourth of the original area.
-44
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 PAIMER,, K.B. PERSON, P.
Effect of Dhderstressing on the Fatigue Cylinder Material - Steel or Aluminum?
Properties of Coarse Flake Graphite Cast Irons APPLIED HYDRAULICS, V 10,pp 111-114, Dec 1957
BRITISH CAST IRON RESEARCH ASSOCIATION, Weight, strength, high-temperature resis-
JOURNAL OF RESEARCH AND DEVELOPMENT, VOL 6, tance, fatigue life as well as application
pp 660-665, June 1957 must all be considered when choosing an
Understressing for 20 x 10^ cycles just below aircraft cylinder material. Relative
fatigue limit did not change the fatigue merits of the two most-commonly used
strength or life or unnotched test pieces; materials are discussede
a slight increase was found in notched test
pieces.

PANSERI, C. and F. GATTO PETERS, R8 Wo and No F0 DOW

Anisotropy and Nonhomogeneity of Fatigue Failure Characteristics of Pressurized
Resistance in High-Strength Light Alloys Stiffened cylinders
ALLUMINO, VOL 26, pp 101-106, March 1957 NACA, USA, ToN 3851, December 1956
Experiments showed fatigue resistance of JOURNAL ROYAL AERO. SOCIETY, ENGLAND 6l,
extruded bars of Avional (Al-Cu-Mg) to be No.556, p 294, April 1957
greater longitudinally than in transverse Stiffened cylinders of 2024 and 7075 alum-
direction and at 45°| moreover samples inum alloysp representative of fuselage
taken from sides of extruded material showed construction,, were tested under internal
a greater resistance than those taken from pressure and cyclic torsion. Fatigue cracks
the center. Anisotropy and nonhomogeneity which developed in the skin resulted in
not found in Ergal (Al-Zu-Jig-Cu). both gradual and explosive types of
failure»

PASETI, A. PETERSON^ Ro E.
Fatigue Limit and Dimensional Effect in Torsion and Tension Relations for Slip
Case of Alternating Tension and Compression Fatigue
(La limite de fatigue et l!effet Grandeur
dans la cas de tension et compression alter- PROCEEDINGS, COLLOQUIUM ON FATIGUE,
nees) STOCKHOIM, SWEDEN, in May 1955, pp 186-194
1956.
CENTRO STUDIO SOLLECIATAZIONI, ITALY, XX METALLURGY ABSTRACTS, ENGLAND 24, Part 8
No. X, pages 17-24, October 1956
REV. METALLURGY, FRANCE 54, No. 4 page 615, April 1957
pp 124-127, April 1957. Peterson shows that for ductile materials,
the ratio bending=»fatigue limit | torsion-
fatigue limit «*3 1/2.

PASEITI, A. PETRENKO, I.P.

Fatigue Limit and Size Effect with Particular Effect of the Degree of Tensile Strain
Reference to Case of Alternating Tensile- and of the Recrystallization Annealing
Compressive Stresses (Italian) Temperature on the Fatigue Limit of
METALLURGIA ITAUANA, VOL 49, pp 523-530 12XH3A Steelo (Russian)
July 1957 Vliianie stepeni deformatsii pri rastiaz-
Principal theories advanced to date in explana- henii i temperatury rekristallizatsionnogo
tion of size effect are reviewed, theory of otzhiga na predel vynoslivosti stali
stress gradients being termed most logical. 12XH3A.
Results of a series of push pull tests on AKADEMII NAUK UKRAINS'KOI RSR, DOPOVIDI
different sized plain and notched specimens No 2, pp 134-137, 1957o
of C20 normalized steel are presented and .45.
analyzed in basis of this preferred theory.
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 PETRUSSEWITSCH, A.I. PLATEAU^ Jo, Go CRUSSARD, J. FAGUET,
G. HENRY, Mo WEISZ, G. SERTOUR, AND
Some Peculiarities of Contact Fatigue Ro ESQUERRE

PROCEEDINGS, COLLOQUIUM ON FATIGUE, Micrographic Study of Surfaces of

STOCKHOIH, SWEDEN, in May 1955, pp 197-208. Material Failed Under Fatigue (Etude
1956 micrographique des surfaces de rupture
METALLURGY ABSTRACTS, ENGLAND 24, par fatigue)
Part 8, page 615, April 1957 REVo ALUMINIM, FRANCE 34, No. 246
page 796^ September 1957

PHILLIPS, C.E. PCMEY, JACQUES, ET AL

Some Observations on the Propagation of Effect of Fine Graphite Grain Distribution
Fatigue Cracks and Granular Structure on the Endurance
of Castings Against Alternating Stresses
PROCEEDINGS, COLLOQUIUM ON FATIGUE, (French) Influence de la finesse de reparti-
STOCKHOIM, SWEDEN, in May 1955, pp 201-217 tion des fontes aux efforts alternes.
1956 and METALLUBY ABSTRACTS, ENGLAND 24,
Part 8, p 642, April 1957 CCHPTES RENDUS, V 245, No. 16,
pp '1311-1314, October 14, 1957
In notched specimens of aluminum alloys Limit of endurance during rotary flexion
subjected to combined torsion and bending of pearlitic castings with nodular,
fatigue, the cracks formed were all the spheroidal or diffused graphite. An ana-
principal stress, regardless of the ratio log method was used to show the import-
of principal tension stress to principal ance of the strain gradient.

.Cont'd Some Observations on the Propagation POPE, J.A., B.K.FOSTER, AND N.T.BLOOMER
shear stress. The direction of the small Limited Life Designs A Survey of the
cracks found in V-notches by Frost (ENGINEER, Problem
ENGLAND 200, pp 464-501, 1955) cannot there-
fore be attributed to dominating effects of ENGINEERING9 BRITISH, VOL 184, pp236-241
shear stress in crack propagation. August 235 1957
Phillips evolved a technique for fatigue- Describes conditions under which design
cracking unnotched specimens and stopping for fatigue should be used. Discusses
the machine before the crack had penetrated effects of scatter of results, stress
appreciably; only one crack was found in raisers and cumulative damage on design
aluminum alloys and Ni-Cr steel, but many methods based on S-N information. Illus-
in copper. trates the approach by an example. Discus-
ses statistical approach to using fatigue
test results.

PLANTEMA, F.J. POPE, Jo Ao, B. Ko FOSTER, AND N.T.BLOCMER

Some Investigations on Cumulative Damage Limited Life Design: A Survey of the
(in Alclad 24S-T Aluminum Alloy) Problem
PROCEEDINGS, COLLOQUIUM ON FATIGUE, ENGINEERING, BRITISH, VOL 184, pp275-278
STOCKHOIM, SWEDEN, in May 1955, PP 218-228, August 30, 1957
1956. METALLURGICAL ABSTRACTS, ENGLAND,
24, Part 8, p 619, April 1957 Continues the discussion of the applica-
tion of statistics to S-N data.
Plantema reports fatigue tests on unnotched Describes Weibull8s method, and briefly
and notched sheets, and riveted joints. discusses the application to complex
The results are compared with those expected structures and fail-safe design.
from Miner's hypothesis (JOURNAL APPLIED
MECHANICS, USA, 12, p A-159, 1945) A high
pre-stress followed by a lower test stress -46-
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PRENOSIL, BOHUMIL RATHBI, K.R. and JENNIFER LONGSQN
Influence of Residual Austenite in Car- Some Fatigue Characteristics of a Two
burized Layers on Behavior Under Alter- Spar Light Alloy Structure (Meteor Tailplane)
nating Stresses (Czech - English, French
German abstract) AERONAUTICAL RESEARCH COUNCIL, ENGLAND
PAPER NO. 258, January 1956
HUTNICKE USTY, VOL 12, pp 704-711, 1957 AIRCRAFT ENGINEERING, ENGLAND, 29, No 335
Influence of residual austenite in car- page 27, January 1957
burized layers of alloy steels on the en-
durance limit-under alternating stressing; Results are given for fatigue tests on
compares endurance limits of specimens in 61 Meteor tailplanes, treated as repre-
which residual austenite is removed by low- sentative small-scale wing systems and
temperature treatment with untreated speci- tested and tested under a variety of load-
mens. ing conditionso The object of the investi-

HAMSEY, P. Wo and D. P. KKDZIE sCont'd Some Fatigue Characteristics, etc.

gation was to study the fatigue character-
Prot Fatigue Study of an Aircraft Steel istics of a typical aircraft structure, in
in the Ultra High Strength Range particular the effects of mean load ,and
JOURNAL OF METALS, V 9, sec 2; AMERICAN alternating load on the endurance. The ef-
INSTITUTE OF MINING AND METALLURGICAL fects of preloading, periodic overloading
ENGINEERS, TRANSACTIONS, V 209, pp401-406 and low temperatures were also investigated.
April 1957. Endurance curves are given for different
mean loads; the results indicate that, for
Fatigue data for a Ni-Cr-Mo-V steel a given alternating load, the endurance is
(AMS-6434) in the tensile strength range roughly inversely proportional to mean load.
up to 280 ksi. The endurance at low temperature is higher
than at room temperature,,

RANSCH, J.T. RAYMOND, JACQUESSON and JACQUES DE FOUGUET

Crystallographic Behavior of Slightly
A Guide to Statistical Methods for Use in Carburized Steel during High Temperature
Fatigue Testing Fatigue Tests (t 800°),(Comportement
cristallographique d'un acier faiblement,
PROCEEDINGS, COLLOQUIUM ON FATIGUE, carbure au cours d'essais de fatigue a
STOCKHOIM, SWEDEN, in May 1955, chaud (t 800°)
pp 269-277, 1956.
METALLURGY ABSTRACTS, ENGLAND 24, OQMPTES RENDUS, FRANCE 244, No. 18
Part 8, page 659, April 1957 pp 2306-2308, April 1957

RASKIN, R. M. and R. A. BAQXAMOV REBESKI, H.

Influence of Asymmetrical Loading Upon A New Design of Wing Based on Metal
the Corrosion Fatigue Resistance of Bonding
Pumping Rods (Russian)
ALUMINUM, p 723, November 1957
VESTNIK MASHINOSTROENIIA, VOL 37, No. 1
pp 28-30, January 1957 Describes in detail the bonding and
assembly of aircraft wings using
"Redux11, which are distinguished by
surface smoothness and high fatigue
strength.
-47-
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 BECCA, P.F. and JBED W. SMITH ROBINSON, GoH.
A Simplified Approach to Design and Effect of Surface Condition on the
Specification of Small Extension Springs Fatigue Resistance of Hardened Steel
MACHINE EESIGH, V 29, pp 102-108 May 2,1957 AMERICAN SOCIETY FOR METALS PUBLICATION
pp 11-46, 1957
Deals with springs for operation under
fatigue load conditions where space is
at a premium.

BEEMOND, J 0 C. BOONBT, BOBERT J e

Titanium Carbide The Effect of Various Machining Processes

on the Reversed-Bending Fatigue Strength
PRODUCT ENGINEERING, pp 84-86, tfov.ll, 1957 of A-110 at Titanium Alloy Sheet
WADC TECHNICAL REPORT 57-310
Discusses various properties and give ASTIA DOCUMENT NO. AD 142118, Nov 1957
design tips* Table includes values
for fatigue strengths at room temperature, Results of reversed cantilever bending
1600° and 1800° F. fatigue tests on A-110 AT (5#Al-2/5^ Sn)
titanium alloy sheet, machined by various
processes are presented. The effect of
shot-peening on the fatigue strength of
the as-rolled alloy is also presented.

RICHART, F.E, ROSENFELD, M0S0

Probabilities in Fatigue Testing
METAL PROGRESS, VOL 72, No. 2, p 111 Fatigue Tests of Model F2H-2, -3, -4
August 1957 Aircraft Wings
Ten fatigue specimens, cut from the same AERONAUTIC STRUCTURE LABORATORY,
bar of metal, at the same stress level NAVAL AIR MATERIALS CENTER, PHILADELPHIA
will show a wide scatter in number of NAMC-ASL-100, 1957
cycles to failure. A method of assessing
probability of failure is arrived at Approximately 11 complete wings were
statistically. fatigue tested to determine whether
service cracks indicated a critical prob-
lem and to developo

ROBERTS, J.G. AND R. L. MATTSON RUBO, Eo

Fatigue Durability of Carburized Steels Fatigue Bending Tests on Steel to Deter-
mine Its Sensitivity to Snbrittlement
AMERICAN SOCIETY FOR METALS PUBLICATION
pp 68-105, 1957 Z. DER DEUTSCHER INGENIENURE, GERMANY 98
No. 17, pp 913-919, June 1956, and
CORROSION, USA, 13, No. 8, page 130
August 1957

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RUDNITSKI, V.I. SAKURAI, T., T. KAWASAKI, and Y. KITA

Fatigue Tests for Gear Wheels Change of Properties of Steel Caused

by Low Temperature Quenching (Japanese)
ZAVODSKAIA LABORIATORUA, VOL 23, No. 11 JAPAN SOCIETY OF MECHANICAL ENGINEERS
PP 1383-1334, 1957 TRANSACTIONS, VOL 23, pp 489-494,
July 1957
Discusses various factors affecting fatigue
strength of gear wheels during bending. Improvement of notch fatigue strength

RYBASENKO, I.D. SALVAGGI, J.

Intermittent Stressing and Heating Tests
Influence of Carbon on Fatigue Limit of of Aircraft Structural Metals
Carburizing Steel. (Russian) Vliianie
ugleroda na predel ustalosti tsementeumoi CORNELL AERONAUTICAL LAB,, INC.
stali. WRIGHT AIR DEVELOPMENT CENTER, U,So
METALLOVEDENIE I OBRABOTKA METALLOV, OFFICE OF TECHNICAL SERVICES, PB 131210,
Noo 10, pp 19-21, October 1957 76 p., May 1957 $2000
Investigation of two steels to determine the C-nCM titanium, A-70 titanium, type-321
effect of C on strength under alternating stainless, N-155 alloy and 4130 steel
loads (sinusoidal stresses). The fatigue were evaluated under conditions of com-
strength of steels, with a surface concentra- bined intermittent temperature and load»
tion of !.}£ C increases with an increase of Analysis disclosed little difference in
internal C content.

SAD3IEK, JOS. and A. KORNEL iCont'd Intermittent Stressing and, etc,

Fractures of Crank-Shafts in Large Piston creep and rupture behavior relative to
Compressors Caused by Fatigue (Czech) the intermittent-load or intermittent-
Unavove lomy klikovych hridelu velkych heat results, Basic mechanisms appear
pistovych kompresoru. to be unaffected by the phase relation-
ships of the combined cyclic-load and
STROJIRENSTVI, V 7, pp 497-501, July 1957 temperature conditions of the study.

SAFEE, WESLEY W. SCHAUB, C., W. LIEDTKE

Peening Cuts Stresses in Plated Parts
The Mechanism of Fatigue Fracture of
PRODUCT ENGINEERING, V 28, pp 92-93, Dec.1957 Metallic Materials
The peening method pounds surfaces of high- PROCEEDINGS COLLOQUIUM ON FATIGUE,
strength steel with shot to neutralize STOCKHOIM, SWEDEN, in May 1955
stresses caused by electroplating, espec- pp 244-250, 1956. and METALURGY
ially chrome plating. It prevents cracks ABSTRACTS, ENGLAND 24, Part 8, page 641
and increases fatigue life of parts. April 1957
Authors maintain that in fatigue there
are formed local plastically deformed
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SCHIJVB, J., AND F. A. JACOBS SCHIJVE, J.
Research on Cumulative Damage in Fatigue The Fatigue Strength of Riveted Joints
of Riveted Aluminum Alloy Joints and lAigs (De vermoeiingssterkte van Klink-
verbindingen en pengatverbindingen)
N.LJUREPORT M 1999, January 1956 and NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS
JOURNAL ROIAL AERONAUTICAL SOCIETY,ENGLAND USA, TECHNICAL MEMORANDUM No. 1395, Aug 1956
61, No.556, page 294, April 1957 AIRCRAFT ENGINEERING, ENGLAND 29, No. 336
Two-step tests and interval tests were per- p.60, February 1957
formed on 24 S-T Alclad riveted lap Joints This report deals with a number of tests on
to study the cumulation of fatigue damage riveted joints and lugs for the purpose of
in this type of joint and to verify the comparing the several types of riveted joints
linear cumulative damage rule. and to study the effect of various factors
on the fatigue strength of lugs.
tCont'd Research on Cumulative Damage, etc.
SCHOLL, HERERT
Available data on light alloy specimens
are reviewed and compared with the results Reciprocal Deformation of Aluminum Single
of the present investigation. Some proposed Crystals (¥echselverformlung von Aluminum-
cumulative damage rules are discussed with Einkristallen)
respect to the experimental results and METALUOJNDE, GERMANY 48, No.5, pp 253-262
general accepted features of the fatigue May 1957
phenomenon. Some remarks are made on the
life estimation of structures under service Single crystals of 99«99/6 purity aluminum
loading. Proposals for further investiga- were subjected, at room temperature to
tion are made. alternating shearing stresses. The ampli-
tude of deformation was set at constant val-
ues ranging from 105 to 8.25#, while the
rate of deformation was kept constant also.

SCHIJVE, J. and F. A. JACOBS SERENSEN, S.V* and M. E. GARF

The Fatigue Strength of Aluminum Alloy Lugs Determination of Dynamical Loading in
NATIONAL LUCHTVAARTLABORATORIUM, RAPPORT Full-Size Fatigue Tests and Some Results
NLL-TNM 2024, 50 p, January 1957
(TL526.N3 N 38.5r Contin) AMERICAN SOCIETY FDR TESTING MATERIALS
STP 216, page 142, 1957
Fatigue diagrams were established for un-
notched specimens and two types of lugs Paper presented at a symposium on large
of 2024-T Al alloy. The stress concentra- fatigue-testing machines at the 60th
tion factors for the lugs are 2.65 and 3.5 Annual Meeting of the ASTM.
respectively.

SHANLEY, F.R, SHANLEY, F.R..

A Proposed Mechanism of Fatigue Failure On the Mechanism of Fatigue
PROCEEDINGS COLLOQUIUM ON FATIGUE, AIRCRAFT ENGINEERING, VOL 29, pp 11-12
STOCKHOIM, SWEDEN, in May 1955, PP 251-258, January 1957
1956, and METALLURGY ABSTRACTS, ENGLAND 24,
Part 8, p 641, April 1957 Discussion on the unbending of atoms
by the repeated application of stresses
Shanley proposes a mechanism by which, after well below the nominal ultimate tensile
plastic slip in the interior has begun, a strength.
localized high stress arises between surface
and atoms and breaks the bonds between them*
It is assumed that the surface slip is re- -5 >-
versed.
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SHAKIEY, F.R» SHEIN, A*S.
Fatigue of Metals the Effect of Fiber Orientation on the
AIRCRAFT ENGINEERING, ENGLAND 29, No.339 Contact Fatigue Strength of Hardened Steel
page 138, May 1957 (Cf Abst. 814; 1957) (Russian) Vliianie orientirovki volokon
na kontaktnuiu ustalostnuiu prochnost1
Recent trends in research on fatigue theory zakalennoi stali
are summarized. It is said that one of METALLOVEDENIE I OBRABOTKA METALLOV, No 12
the latest developments is the analysis of pp 61-66, December 1957
the fatigue crack formation in terms of dis-
location theory. For this purpose models Examples prove that transverse orientation
have been proposed which represent the be- of fibers increases steel strength by
havior of dislocations under cyclic loading, 20#, and its contact fatigue strength by
3 to 5 times.

sCont'd Fatigue of Metals

SHEPPABD, A.W.
particularly in the neighborhood of a free
surface or void. 5y giving a hypothetical Contour Etching
account of what ma^ happen in a polycrystal-
line material under cyclic loading, a con- ICACHINERY, VOL 90, pp 153-159, Jan 18,1957
densed interpretation of the unbending
theory is presented. The significance of Fatigue results are similar for machine
the progressive unbending theory is seen and contour etched specimens
in the fact that it explains both the initi-
ation and the growth of the crack initiation
leaving the most important part of the prob-
lem unsolved.

SHANLET, F.R. SHISHKIN, V. YD, V. A. MAKORIN, and

R»Z. MAN3UOVA
On the Mechanism of Fatigue
AIRCRAFT ENGINEERING, ENGLAND 29, No.335 A Study of Tee Joints Under Fatigue
pp 11-12, January 1957. Loading
Although the original paper discussed by SVAHDCHNOE PROIZVODSTVO, USSE, June 1956
Shanley deals with fatigue in copper alone and WELDING AND METAL FAB*, ENGLAND 25,
(The Origin of Fatigue Fracture in Copper, No. 10, p 405, October 1957
N. Thomson, N. Wadsworth, and N. Louat, Philo-
sophical Magazine, England 1, Series 8, No 2,
February 1956). The fundamental research
conducted in this field is of a general
character.

Cont'd On the Mechanism of Fatigue SIEBEL, E. and H. GAIEE

Experimental proof is cited to show that Influence of Surface Roughness on the
surface effects are a part of the basic Fatigue Strength of Steels and Non-
mechanism of fatigue. Ferrous Alloys
Crack formation'theories advanced by ENGINEERING DIGEST, VOL 18, March 1957
different research workers are critically From a series of steels and non-ferrous
surveyed. alloys in a specified heat treated con-
dition, fatigue test specimens were
machined to a specified degree of surface
roughness and were tested in push-^poH
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STICKLET, G. W. and MILLER, J. L.
Contfd The Physical Properties of...
Fatigue Properties of Two Alundnum Die
Casting Alloys suggested, or the use of a softer undercoat,
such as lead. Heating high tensile steels
MODERN CASTINGS, USA 32 no. 1, p 51, July 1957 after chromium plating, to relieve hydrogen
Paper presented at the 6lst Castings Congress embrittlement, should be avoided if cyclic
of the American Foundrymen's Society. stresses are important, unless a temperature
of at least 440°C can be tolerated. Zinc
The results obtained in reversed bending and plating is beneficial since it normally
axial stress fatigue tests of aluminum die contains compressive stressese
casting alloys 218 and 380 are given. No
correlation was found between tensile

Cont'd Fatigue Properties of Two Aluminum... SUZUKI, J.

strength and fatigue strength. Fatigue Strain Figures Appearing on the Surface of
strength decreased with increasing tempera- Copper Electrodeposits Subjected to Fatigue
ture and is reduced by notches. The authors
found that die cast cylinder heads of either JOURNAL INST. METALS, ENGLAND 85, Part 5,
alloy functioned satisfactorily under the pp 206-208, January 1957
repeated stress at elevated temperature The effects of the microstructure of the
characteristic of this application. underlying metal upon the flecks and strain
figures appearing on the surface of electro-
plated copper subjected to fatigue have been
investigated. Flecks do not occur at random
positions, but appear in the region of the

STUBBINGTON, C. A. and P. J. E. FORSYTH Cont'd Strain Figures Appearing on the «.»

Some Metallographic Observations on the grain boundaries of the metal beneath.

Fatigue Behavior of Copper and Nickel and Moreover, the grain boundaries on which the
Certain of Their Alloys. flecks appear run parallel to the directions
of the planes of the maximum shear stress.
INSTITUTE OF METALS, JOURNAL, V 86, The maximum shear strain at the surface of
Oct. 1957, pp 90-94 the electrodeposited copper coatings below
which no flecks occur has a certain limiting
value under constant conditions of testing.

SUCH, T. E.
The Physical Properties of Electrodeposited TARASOV, L. P.
Metals
MATALLURGIA, V 56, No 334, PP 61-66, Aug. 1957 How Grinding Affects Fatigue Strength
Author mentions the effect of electrodeposit- AMERICAN MACHINIST, V 101, pp 72-74
ed metal on fatigue strength. Nickel and December 30, 1957
chromium, with high internal tensile stresses
are worst offenders. Both can be deposited,
however, under certain conditions with
internal compressive stresses. Alternatively
shot-peening the plated component is
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SINCLAIR, G. M., CORTEN, H. T., and DOLAN, T.J,
ContM Recent Researches on Fatigue at the...
Effect of Surface Finish on the Fatigue
Strength of Titanium Alloys RC 130B and TI3/0A improved by using pins with interference fits
in the tongue. Fatigue tests have been made
ASME TRANSACTIONS, p 89, January 1957 on screw-threads. Al-Mg alloys have been
An investigation was made of the effect of tested under high plane-bending stresses.
various surface-finishing operations on the
fatigue strength of two titanium alloys, RC
130B and Ti 140A. The types of finish studied
included roughs-machined, machined and mechani-
cally polished, cold-rolled electropolished,
and ground surfaces«

Cont'd Effect of Surface Finish on the ... STARKEY, V. Lo, MARCO, S.M.
In general the fatigue strength for lifetimes Effects of Complex Stress-Time Cycles on the
exceeding 2 x 10' cycles was found to vary Fatigue Properties of Metals
according to the hardness of the surface
layer with the highest hardness corresponding ASME TRANSACTIONS, p 1329, August 1957
to the greatest fatigue strength. Tabulated An investigation was conducted to determine
data, graphs, and speciman and apparatus the effects of complex stress-time cycles
detail diagrams. on the fatigue properties of metals. The
uniaxial stresses studied were complex in
the sense that their stress-time patterns may
be analyzed as composed of several harmonic
components. Four theoretical design methods,
and the results of an experimental investi-
gation involving complex stresses are

Confd Effects of Complex Stress-Time...

SMITH, C. R.
The Fatigue Strength of fiiveted Joints presenteda Comparisons are made of the test
AIRCRAFT ENGINEERING, V 29, Feb 1957, results with the theory predictions. Report
contains graphs and schematic diagram of
PP 34-38. testing machine.
The factors influencing the fatigue strength
of a riveted joint are discussed along with
methods to improve the fatigue strength. The
results of fatigue tests and strain measure-
ments of riveted joints along with suggestions
for improved joint designs are presented.
2 references, 6 photographs, 12 graphs and
sketches.

SOPHITH, D. G. SYRE, R.
Recent Researches on Fatigue at the Mechanical Heat Resistance Behavior of Titanium and Its
Engineering Research Laboratory, East Kilbride Alloys, (French) Le comportement a chaud du
PROCEEDINGS COLLOQUIUM ON FATIGUE, STOCKHODC, titane et de ses alliages
SWEDEN in May 1955, PP 260-268. 1956. METAUX, CORROSION-INDUSTRIES, V. 32, May 1957
METALLURGY ABSTRACTS, ENGLAND 24, Part 8> pp 201-207
p 615, April 1957
Tensile and fatigue properties of commercial
For the effect of size on the fatigue strength alloys at elevated temperatures. Good result!
of aluminium alloys, see Phillips and Fenner, were obtained with alloys containing A10
Proc. Inst. Mechanical Eng., England 165, p 12%
1951. A by
Copyright joint
ASTMconsisting ofreserved);
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Tue Dec 29 16:13:34 EST 2015
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has a very
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SMITH, C. R. STAUMEHER, J, E., MUNSE, W. H. and B. J.
GOODAL
Fhotostress Plastic for Measuring Stress
Distribution Around Rivets Behavior of Welded Built-Up Beams under
Repeated Loads.
REPORT BY CONVAIR, SAN DIEGO-A Division of WELDING JOURNAL, V 36, January 1957
General Dynamics Corporation 1957 Small A373 steel beams manually welded using
E7016 electrodes and a backstepping welding
procedure, and field splice configurations
were fatigue tested in comparison with
A373 steel as received.

SMITH, G. G. STARKEY, MARCO, and GATTS

The Initial Fatigue Crack
Determination of the effect of fatigue
ROYAL SOCIETY PROCEEDINGS, V. 242, ser A, cracks on the fatigue properties of
Oct. 29, 1957 PP 139-197 + 3 plates metals.
Considers the formation of persistent slip
bands during cyclic stressing and their dev- FINAL REPORT BY THE OHIO STATE UNIVERSITY
elopment into fatigue cracks. In Cu and Al RESEARCH FOUNDATION, RF PROJECT 6l6, 31
at low temperatures fatigue cracks appear to July 1957.
be formed in this way; at room temperature
in Al they may form also along grain
boundaries.

SMITH and LINDENEAU STEFFENS, H. D.

Riveted-Joints Fatigue Strength Fatigue Studies on Bonded Aluminum
Structural Parts
ASTM STP-203, P 10, 1957
ALUMINUM p 783, December 1957-
In fatigue behavior, bonded structures may
differ considerably from small specimens.
Describes behavior of bonded extruded
sections at high loads in fatigue (rotating
bend) tests of specimens 1 m Iong0

SOPWITH, D. G. and FIELD, J. E. Cont'd Fatigue Studies on Bonded Aluminum,.

Unification of Screw Thread Practice

By using flexible interlayers, considerably
THE ENGINEER, V. 203, pp 793-795 higher fatigue limits were obtained than wit
(May 24, 1957) straight bonding or riveting* In design of
bonded parts, it is important to avoid sud-
Summary of work at National Physical den changes in bending moment*
Laboratory, including axial fatigue tests.

-54-
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ST^RKEY, MARCO, and COLLINS (OSU) TARASOV, Lo P., HYLER, Wo S« and LEN12ER, H.R.
The Effect of Fretting on Fatigue Character- Effect of Grinding Conditions and Resultant
istics of Titanium-Steel and Steel-Steel Joints Residual Stresses on the Fatigue Strength
of Hardened Steel
ASME PAPER No 57-A—113, December 1-6, 1957 AS1M REPRINT No. 65, 1957 Annual Meeting
Fretting is a phenomenon resulting from the Reversed plane bending fatigue tests were
small-amplitude cyclic relative sliding motion carried out on flat test pieces of modified
at the interface between two solid bodies AISI 52100 (Re 59) at cpm to study the effect
pressed together by a normal force. Fretting of grinding variables0 Residual stresses
persists in machine joints such as bolted were studied by a deflection method as suc-
joints, riveted joints, interference fits, cessive layers were etched away. The surface
antifriction bearings, leaf springs, wire stress ranged from compression to tension,

Cont'd The Effect of Fretting on Fatigue.„. Cont'd Effect of Grinding Conditions0„„

ropes, etc. The objective of this investigatioi depending on grinding conditions, but the
was to obtain a quantitative evolution of the peak tensile stress was slightly subsurface.
fatigue damage caused by fretting titanium For good commercial grinding conditions, the
against steel. The effect of shot-peening and fatigue strength was the same as for gentle
cold-rolling as fretting fatigue inhibitors grinding! severe grinding caused a decrease oj
were evaluated. Results of the investigation about 13%9 whereas with some straight grind-
are discussed in terms of the probable basic ing oils increases of up to 38$ were observed,
mechanisms of fretting and fatigue phenomena Residual peak tensile stresses up to about
and the effects of prior cold-working on these 50,000 psi had little effect,, Cyclic stress-
phenomena. ing did not reduce the magnitude of the
residual stresses„

SWATS, D. E.> and FRANK, R. C.

Fatigue Life as a Function of Surface
Conditions TAYLOR, D. B. , and TADROS, A. Z ,
METALLURGIA, V 56, No. 337, p 230, Dec 1957 Tension and Torsion Properties of Some Metals
Short note on the effect of lubricating oil under Repeated Dynamic Loading (Impact)
applied to the surface of fatigue specimens of
SAE52100 steel.* Six R.R. Moore test-pieces PROCEEDINGS OF INST. OF MECHANICAL ENGINEERS,
were liberally coated with oil, and six were V 170, 1956
'thoroughly cleaned with acetone and alcohol.
All test-pieces were then tested at 125,000
psi in the same machine in random order. The
-oil-free test-pieces had significantly shorter
lives than the'oiled test-pieces.
TAKEUCHI, K.
On the Fatigue Behavior of Commercially Pure TAYLOR, R. J.
Titanium, (Japanese)
Experimental Design and Methods of Analysis
LIGHT METALS (TOKYO), V. 7, May 1957 Used in Studying Effects of Metallurgical
Variation on Failure
Mean stress versus fatigue properties were
studied for annealed and 50 percent cold-rolled PROCEEDINGS COLLOQUIUM ON FATIGUE, STOCKHOLM,
titanium sheet on Schenkfs vibrating sheet SWEDEN in May 1955, PP 269-277, 1956,
bending machine. METALLURGY ABSTRACTS, ENGLAND 24, Part 8
p 659, April 1957
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TEED, P, L« Cont*d The Origin of Fatigue Fracture...
visible, and these persistent bands grew
The Fatigue of Aircraft with further fatiguing, and at about half
the fatigue life they had spread into more
'MACHINERY LLOYD, OVERSEAS EDITION, v 29 (4) than one grain and were clearly cracks.
PP 70-73, 75-53, 1957 Tests on single crystals gave similar effects
The persistent slip bands were associated
Referring to aluminum alloys and wrought alum- with the surface, and a deep electropolish
inum parts used in airframe construction. (30n) removed them completely. By such a
Quotes test data derived mainly from the polish every 25% of the normal life a
Royal Aircraft Establishment deals primarily specimen was tested in fatigue to 225$ of
with the stress concentrations and built-in the normal life, and did not even then seem
stress. altered under a microscope.

THOMPSON, N. and WADSWORTH N0 Jo

TEED, P. L. Structural Changes and Energy Dissipation
During Fatigue in Copper
Why Metals Fatigue BRITISH JOURNAL OF APPLIED PHYSICS, SUPPLI-
MENT No. 6S Physics of Non-Destructive
THE NEW SCIENTIST, ENGLAND, No. 1? PP 30-32, Testing, 1957
March 14, 1957
Apparatus and methods used and summary
results of observations made of metallo-
graphic and energy dissipation changes
occurring during fatigue testing of fully
annealed copper.

THOMAS, H. THURSTON, R. C. A.
Fatigue and Welding Technique (Dutch)
Vermoeiing en lastechniek. Mechanism of Fatigue; A Review
3MIT MEDEAELING3N, V 12, No. 3, July-Sept. CANADIAN MINING AND METALLURGICAL BULLETIN,
1957, pp 97-107 V 50, pp 70S-716, December 1957
A survey of fatigue tests covering simple weld
connections as well as rather complete Present day theory of dislocations
structures. Welding faults, irregularities at mechanism of slip initiative of fatigue
the plate surface, and faulty construction cracks, subsequent propagation.
influence fatigue life.

THOMPSON, N., WADSWORTH, N., and LOUAT, N. UZHIF, GALPERIN, and ZOOYKOVA
The origin of Fatigue Fracture in Copper
PHILOSOPHICAL MAGAZINE, USA 1, No. 2, pp 113- Sudden Fracture of Machine Parts and
126, 1956, METALLURGY ABSTRACTS, ENGLAND 24, Structure Elements
Part 7, p 575, March 1957 ASOM STP 216, p 132, 1957
Specimens of copper were tested in push-pull
at 1000 c/s., and microscopic examination of Paper presented at a symposium on large
the surface was carried out at various stages fatigue-testing machines at the ASlM's
of the fatigue life. After some 5% of the 60th Annual meeting.
fatigue life of polycrystalized copper, an
electropolishing technique which removed
ordinary slip
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UZHEC, a. v. VALLURI, So R. -
Contribution to the Theory of Fatigue Fatigue and laternal Friction of Aluminum
PROCEEDINGS COLLOQUIUM ON FATIGUE, STOCKHOIM, NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS
SWEDEN in May 1955, PP 278-287, 1956. TECHNICAL NOTE 3755, USA, Sept. 1956
METALLURGY ABSTRACTS, ENGLAND 24, Part 8,
p 614, April 1957 Investigation of the internal friction and
fatigue strength of commercially pure 1100
Uzhik discusses the conditions for the inital aluminum under repeated stressing torsion
plastic deformation in a zone of stress concen- at various temperatures and stress levels
tration, and the redistribution of stresses at indicated the existence of a critical tem-
the elastic-plastic stage of deformation. perature at which the fatigue life of a

Cont'd Contribution to the Theory of .,. Cont!d Fatigue and Internal Friction.„»
Experiments on steel have shown that cyclic specimen reaches a minimum value. The
loading gives, in the stress-concentration zone, effect of this temperature on the internal
a continuous increase in shearing strength friction at various stress levels was
accompanied by a corresponding increase in substantial.
stressesj it appears that simultaneously there
is a substantial lowering of resistance to PRODUCT ENGINEERING, USA 28, No. 7 p 358,
rupture in some very small areas. July 1957

VALLURI, S0 Fo
VIDAL, Go, GIRARD, F0, and LANUSSE, P0
Effect of Frequency and Temperature on Fatigue
of Metals Machine for Fatigue Microtesting Under
NACA TN 3972, February 1957 Tensile - Compressive Load Altering at
6000 Co/see. Mieromachine d'essais de
On the basis of the "standard linear solid" fatigue en traction - compression a 6000
model, it seems possible to conclude from alternaees par seconde.
phenomenological considerations that the
critical temperatures observed by Daniels and REV. ALUMINUM (FRANCE) 34, No. 246, p 796,
Dorn and by Valluri are not real critical September 1957
values but are simple temperatures associated
with corresponding frequencies of fatigue
stressing above which the fatigue behavior
changes. It is suggested that the reason why

Cont'd Effect of Frequency and Temperature... VIGLIONE, J.

one does not observe the effect of frequency Fatigue Strength of Bolts
at room temperature in normal engineering PRODUCT ENG., pp 203-205, March 1957
practice is that the critical frequency
associated with room temperature differs subs- Fillets^, circumferential cracks and thread
tantially from those frequencies customarily works are well known sources of fatigue
used in fatigue testing. failure in steel bolts, but longitudinal
flaws which are more difficult to find and
are not readily visible, may be equally
important as a source of failure. Types
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VrDDVEC,.F. H.
Analysis of Dynamic Creep Considering Strain
Hate Effects VYAZNIKOV, No Fo, and ERMAKOV, S0 S0
WRIGHT AIR DEVELOPMENT CENTER MATERIALS Method of Steel Testing for Impact Fatigue
LABORATORY, WADC TECHNICAL REPORT 57-104
16 p9 May 1957 (TL507 Un3*lSw Vis) ZAVODSKAYA LABORATORIA, V 23, pp 1095-1097-
The theoretical analysis of the strain rate Sept. 1957.
effects in dynamic creep conform with the
experimental observation that retardation of
creep increases with increasing temperature,
and with increasing alternating stress
frequency.

WAISMAN and YEN

VOLKOVA, To I.
Effect of Forming on Mechanical Properties
Process of Relaxation Under Condition of
Repeated Stresses (Russian) Metallovedenie i ASTK STP-203* p 67, 1957
Obrabotka Metallov, No, 75 pp 13-18, July 1957 Effects of stretching and bending on the
static and fatigue strengths of sheet metals
Certain mechanical parts which are habitually were determined experimentally on several
exposed to high temperatures or to stresses aluminum alloys, on commercial pure
develop resistance to relaxation* It is desir- titanium^ and on type 302 stainless steel.
able to avoid higher than working temperatures These effects can be explained or predicted
even for a short time between subsequent by considering the effect of three factorss
lurking loads. 6 refs. (l) strain hardening, (2) micrp-residual
stress, and (3) macro-residual stress.

70LIJSRS, Co
Survey of Behavior of Nickel Alloys,
Especially Nickel-Chromium Alloys at High WALKER, P. Bo
Temperatures (Dutch) Overzicht over het gedrag
Van rdkkellegeringen,, in het bijzonder de nik- The Structural Aspect of Aircraft Fatigue
kel~chrcx>m-legerign5 bij hoge temperatuur
METALEN, V 12, pp 302-310, Aug. 31, 1957; THE FATIGUE OF METALS, published by the
pp 342-349, Sept. 16, 1957. Institution of Metallurgists, England 1956,
Oxidation resistance and high-temperature ASTRALASIAN ENGINEER, Astralia 49, No. 3,
Tjorrosion resistance in different gas atmos- p 6S, March 7, 1957
pheres under varying conditions; creep
properties; fatigue; influence of notches.

WARD, Ro Go
VOL3MECKE, A. R. Selection of Aluminum Alloys by Fatigue
Properties
Full-Scale Wing Fatigue Testing AIRCRAFT ENGINEER,
AS1M STP-203, p., 1957 A method of comparing the performance of
different alloy types under fatigue condit-
ions for which complete data are not avail-
able, is presentedo For this purpose the
factor R is introduced and is defined as the
ratio of the fatigue stress of specimens
under the new testing conditions to that of
Copyright by ASTM Int'l (all rights reserved); Tue Dec 29 16:13:34 EST 2015 -58- specimens from the same batch of material
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authorized.
 Cont'd Statistical Handling of Fatigue Data..
WATERHOUSE, R. B.
and analyzed. Formulae for computation of
Corrosion Fatigue the parameters, including the variance in
fatigue strength, have been derived. The
THE FATIGUE OF METALS, Published by the Instit- variances in the parameters have been deduced
ution of Metallurgists, England, 1956. for the purpose of setting fiducial limits.
AUSTRALASIAN ENGINEER, Astralia 49, No. 3, The influence of test numbers on the accuracy
p 68, March 7, 1957. of results, and the best apportionment of
tests among the stress levels have been
discussed. Five series of 4 x 9 tests have
been produced by random drawing from a large
test series of 270 tests. The parameters of
each series have been determined. Means,

JWEAVER, T. D. Cont'd Statistical Handling of Fatigue Data..

Corrosion Fatigue standard deviations, and coefficients of

variation have been computed in order to shed
CHEMISTRY & INDUSTRY, No. 36, pp 1190-1194, some light on the comparative merits of four
Sept. 7, 1957. alternative methods proposed for the deter-
mination of the parameters.
Points out the deleterious effect of combined
corrosion and cyclic stress, the mechanism of AIRCRAFT ENGINEER (ENGLAND) 29, No. 340
failure under such conditions, and the counter- p 187, June 1957
measures which can be taken.

ttEXBULL, WALODDI

WECK, R. Scatter of Fatigue Life and Fatigue Strength

in Aircraft Structural Materials and Parts
Fatigue in Ships
AERONAUTICAL RESEARCH INSTITUTE OF SWEDEN,
SHIPBUILDING AND SHIPPING RECORD (ENGLAND) REPORT 73, 25 p (TL504 F67m Vis) 1957
DESIGN EQUIPMENT, No. 1957, pp 7-8, 1957.
Fatigue properties are described by a simple
S-N curve, derived from experimental work on
steel, Al alloys, and Cu.

WEIBULL, WALODDI
Statistical Handling of Fatigue Data and Plan-
ning of Small Test Series WEIBULL, W,

THE AERONAUTICAL RESEARCH INSTITUTE (SWEDEN) Cumulative Fatigue Damage (French) Donnnages
REPORT No. 69, October 1956. cumulatifs par fatigue

General regression formulae have been adapted REVIEW ALUMINUM, FRANCE 34, NO. 246, p 796,
for the purpose of evaluating date from fatigue September 1957.
test series. The concept of linear regression
imposes
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WEIBULL, WALODDI Cont*-d Basic Aspects of Fatigue...
Static Strength and Fatigue Properties of area of a plate specimen with a cnetral hole
Unnotched Circular 70S-T Specimens Subjected The rate of propagation is independent of
To Repeated Tensile Loading the length of the crack.
THE AERONAUTICAL RESEARCH INSTITUTE (SWEDEN)
REPORT No. 68, June 1956.
Data from a series of 24 static tensile tests
and 270 fatigue tests have been statistically
analyzed by determination of the median S-N
curve, the scatter and the distribution func-
*tion of the fatigue strength as well as the
P_Q_M equation. It was found that the scatter
Cont*d Static Strength and Fatigue...
in fatigue strength is independent of the WEIBULL, Wo and ODQVIST, F. K. G. (German)
number of stress cycles applied and that the
strength is neither normally nor log-normally Fatigue Testing
distributed. The scatter due to the material
is small and of the, same magnitude as the DRIAHT, V &9 pp 429-431, October 1957
scatter due to the testing machine. Formulae
for calculating the variances of estimated A report on an international colloquium on
parameters have been derived and applied to fatigue testing held in Stockholm in
the test data. The explicit formula obtained May 1955 - proceedings and speeches pub-
. for the drag difference between equivalent lished in book.
bodies is essentially the same as that
obtained in linearized supersonic theory by
^Ward and others. The important conclusion to
be drawn is, within the limitations of the

Cont*d Static Strength and Fatigue... WEISMAN, MELILL, and MATSUDA

approximate theory, that the drag of a body, Uni-Directional Axial Tension Fatigue Tests
having its cross-sectional area different of Beryllium Copper and Several Precipita-
from zero at the rear end^ may be considerably tion Hardening Corrosion-Resistant Steels
reduced by spreading out the area in a span-
wise direction leaving the distribution of ASTM STP-203, p 47, 1957
cross sectional area invariant.
AIRCRAFT ENGINEER, ENGLAND 29, No. 340, p 187,
June 1957•

WEIBULL, W.
WELTER, GEORGES, and DUBUC, JULIEN
Basic Aspects of Fatigue
PROCEEDINGS COLLOQUIUM ON FATIGUE, Stockholm Fatigue Resistance of Simulated Nozzles in
Sweden, in May 1955, PP 289-297, 1956. Model Pressure Vessels
METALLURGY ABSTRACTS, England 24, Part 8
pp 641, April 1957. WELDING JOURNAL, V 36, pp 271s-274s,
June 1957.
Weibull applies the concept of cumulative dam-
age to a point of local stress-concentration All fractures occurred in the longitudinal
where a fatigue crack is initiated and to the direction of the pressure vessels and began
tip of the propagating crack. Tests on Alclad at points of maximum circumferential stress
24S-T
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vessel shell.
WELLS, E. W. WHALEY, Ro Bo
Fatigue Loadings in Flight Loads in the Fuselage Fatigue-Crack-Propagation and Residual-Static-
and Nose Under-Carriage of a Varsity Strength Results on Full-Scale Transport-
Airplane Wings
AERONAUTICAL RESEARCH COUNCIL (ENGLAND) REPORT
NO. 287, May 1956 NoA.CoAo (USA) ToNo 3847* December 1956
Flight tests have been made on a Varisty to Results are presented of fatigue-crack prop-
obtain data on the fatigue loads in the fuse- agation during fatigue tests on the wings of
lage and the nose undercarriage. The data C-46 airoplanes. Results are also presented
^are tabulated in terms of the number of load of the residual static strength of these
ranges of a given magnitude occurring during
Cont'd Fatigue Loadings in Flight... Cont * d Fatigue-Crack-Propagation...
various ground and flight conditions. An wings after fatigue tests. The propagation
estimate is made of the loads in a typical curves along with an explanation of the crack
operational training flight to show the relative growth are presented for each wing. Curves
importance of the various conditions. A relfe- also show the trends that occur with changing
tionship is established between the fuselage load levels. The loss in static strength is
loads and the accelerations at the aircraft e.g. also shown and is compared with the calculated
when flying in turblence? this enables the res- strength and the results of small specimen
ults from the flight tests to be linked to tests.
operational data obtained on gusts.
J. ROYAL AERONAUTICAL SOCIETY ( ENGLAND) 6l,
AIRCRAFT ENGINEER (ENGLAND) 29, No. 336, p 59, No. 559, p 508, July 1957.
February 1957

WHITMAN, Jo Go
WESTERWICK, R. Fatigue Properties of Welds
The Roll Coupling Problem. A Mathematical SHEET METAL IND* (ENGLAND) 34, No. 363,
Approach. PP 529-538, July 1957.
This article constitutes one chapter of a book,
AERONAUTICAL ENGINEERING REVIEW V. 16, under the general title of "The Fatigue of
pp 48-51, December 1957 Metalsd0 Various factors which are responsible
for the reduction in fatigue strength of a
A method of determining augmentation of high- welded joint, as compared with an unwelded
performance aircraft to reduce inherent suscep- specimen, are described briefly. The existing
^tibility to inertia coupling. fatigue information on butt and fillet welds
in mild steel is then summarized, with an

WHALEY, RICHARD E.: Gont'd Fatigue Properties of Welds

Fatigue Investigation of Full-Scale Transport-
Airplane Wings. Variable-Amplitude Tests with explanation for the low results quoted,
a Gust-lo~ads Spectrum. particularly for transverse fillet welds.
NACA TN 4132, November 1957-
Crack-initiation frequency of occurrence of
cracks, crack propagation, lifetime to final
failure, and spread in lifetime are investigated
and compared with results from constant-amplitude
tests on similar wings. Information on x-ray |
techniques to determine the presence of cracks '
inCopyright
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WIENE, Po E0 WILKBJS9 E. W. G O
Cumulative Damage in Fatigue
Effect of Annealing (650°C) on Bending Fatigue
of Large Welded Test Pieces„ PROCEEDINGS COLLOQUIUM ON FATIGUE, Stock-
holm, Sweden, in May 19559 pp 321-332, 1956
TYPEWRITTEN DOCUMENT, 19 p and BIBLIOGRAPHICAL METALLURGY ABSTRACTS, England, 24, Part 8,
BULLETIN FOR WELDING (FRANCE) 9, No. 4/6, p 615, April 1957
p 93E, April-June 1957. Wilkins describes tests in which specimens
are subjected to fatigue stresses at one
level and then failed at a higher stress
level^ and comparisons are made with tests

Contfd Cumulative Damage in Fatigue

WILDER, A 0 B. and BENTER, W. P.
Properties of Open-Hearth and Bessemer Seamless in which the higher stress is applied first,
Pipe Preliminary results are reported on a light
alloy.
ASTM PREPRINT No. 67, 1957, (presented at the
Annual Meeting of the Society 1957)
This paper discussed certain properties of car-
bon steel pipe. Capped (rimmed) steels are
customarily used for welded pipe, but in this
instance were rolled into seamless pipe for
^comparison with the killed steels generally
employed in the manufacture of seamless pipe.
All the material tested was made into seamless
jdpe of the same size. Steels made by the basic
open-hearth and acid bessemer process were
Cggji^d Properties of Open-Hearth and ...
investigated. The aging characteristics after WILLIMS5 Co and HAMMOND^ R»A.F*
cold working and also after quenching were
evaluated and the various steel compared. Kie The Change of Fatigue Limit on Chromium or
fatigue properties, impact properties and Nickel Plating with particular reference to
elevated temperature tensile properties were the Strength of the Steel Base
also investigated.
METAL FINISHING JOURNAL (ENGLAND) 3, No. 30
pp 248-253, June 1957

WRIGHT, K. Ho R.
WILKINS, E. W.
Fretting Corrosion as an Engineering
Stress Concentrations in Fatigue (French) Problem,,
Concentrations de contraintes dans la fatigue
CORROSION PREVENTION & CONTROL, V» 4
REVIEW ALUMINUM (FRANCE) 34, No. 246, p 798, PP 37-44, Nov. 1957
September 1957 Characteristics and mechanism of fretting
corrosion; surface treatments and lubrica-
-62- tion as remedial measures; fatigue.
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WOOff, W. 3U and SEGALL, R. L.
Cont*d The Endurance Strength..,
Annealed Metals Under Alternating Plastic Strain1
defects. Even the smallest defects can be
PROCEEDING ROYAL SOCIETY, SERIES A (ENGLAND) 242 detected with present highly developed non-
No. 12229, pp 180-188, October 29, 1957 destructive testso

Annealed metals (copper, nickel, alumininium and

a-brass) were subjected to cycles of small alter-
nating torsion in which the amplitude of plastic
strain was held constant, measurements were made
of the proof stresses required to impose the
successive reversals of strain. Variations in

Gont!d Annealed Metals Under...

this proof stress, which shows how the metal YAMANOUCHI^Ho and INUKAI^T.
strain-hardens at each amplitude, are correlated
with structural changes shown by X-ray diffrac- Fatigue of Carbon Steel by Ultrasonic Flaw
tion and metallographic examination. The Detection Method
results show that the rate of increase of the
strain-hardening which occurs during the early REPORTS CASTINGS RESEARCH LABORATORIES,
cycles decreases during subsequent cycles, WASEDA UNIVERSITY (JAPAN) No. 19 pp 55-58,
indicating that the plastic strain in cyclic October 1956. CORROSION (USA) 13, No. 10,
deformation may be non-hardening* p 150, October 1957.

WOOD, W. A. and SEGALL, R. L. YAMATO, SHIGEO, and MORIKAWA, K.

Fine Slip and Fatigue Cracking, Letter to the Fatigue Rupture Study by Metallography (Japan-
Editor
ese)
JOURNAL INSTITUTE METALS (ENGLAND) 3, Part 19,
pp 160-161, March 1957 JAPAN SOCIETY OF MECHANICAL ENGINEERS,
Surface contour developed across typical slip JOURNAL, V 60, May 1957
bands was determined using an electropolished Fatigue rupture study of low and high-carbon
Specimen subjected to fatigue deformation. The steel by microscopy. Majority of tests
taper section was taken making an angle with the were made on rail-road car wheeleL
specimen surface of about 3°* which confers on
pontour changes perpendicular to the surface a
geometrical magnification of about 30 times.

WUPPERMANN, A. TOEODCR YOKOBORI, To

A Theoretical Criterion for the Fracture of
The Endurance Strength of Crankshafts and Its Metals Under Combined Alternating Stresses
Assessment by Acceptance Tests. (German)
Die Dauerhaltbarkeit von Kurbelwellen und ihre JOURNAL OF APPLIED MECHANICS, V 24, pp 77-80
Beurteilung in Ablieferungspriifungen. March 1957
STAHL UND EISEN, V. 77, PP 1117-1122, Aug. 22, A criterion is developed on the basis of the
1957 present concepts of dislocation. These con-
cepts are modified by taking into account
Segregations in the ingot closed by forging show the stress concentration by the inclusion it-
upCopyright
after finishing as longitudinal surface self against which dislocations pile up.
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ZJ&EK, J*. M» WEISZ, Mo, Fo BASTENAIRE AND B0 CA&UD
Accelerated Fatigue Testing of Polymethyl Meth- Statistical Fatigue Tests by the Method
acrylate. of the Progressive Charge
BRITISH PLASTICS, V 30, pp 399 + 4 pages PROCEEDINGS, COLLOQUIUM ON FATIGUE,
STOCKH01M, SWEDEN in May 1955* pp 14-23,
Prot's "progressive load" method was successful 1956
ly used. The hysteresis loss is high in poly- METALLURGY ABSTRACTS, ENGLAND 2ks
methyl methacrylate. This, together with the Part 8, page 659* April 1957.
low heat conductivity of the material, means
that rapid cyclic stressing gives an apprecible

Gont'd Accelerated Fatigue Testing...

temperature rise of the specimen, giving a wide
range for the fatigue limit.

ZAUSTIN, M. V.
On the Necessity of Fundamental- and Widened
Hesearch in Strength of Materials
ASTM BULLETIN, No. 226, pp 52-61, Dec. 1957
Suggestions for the improvement of methods of
testing metal from the point of view of tension^
compression, shear strength, impact, stress,
ductility, fatigue, to enable more efficient
design. 11 ref.

ZILOVA, T. K., SADOVSKir, V.E. and DMINA, N.I,

Effect of Surface Conditions of Steel 30KhGSA
on Tendency Toward Fatigue (Russian)
METALLOVEDENI OBRATETKA METALLOV, No. 8,
Aug. 1957.
Sensitivity of this steel toward fatigue
increases when its surface is hardened either
by heat or mechanical treatment.
-64-
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