6.3.
Presentation of data
6. 3.1. aerodynamic coefficients Tables: 3. 4/ 3. 5
Figure. : 3.6
6. 3.2. surface pressure Tables: 3. 4/ 3. 5
Figures: 3. 713. 813. 9
6. 3.3. boundary l a y e r quantities Table: 3. 6
Figure: 3. 10
Schlieren pictures: Figure 3. 10
6 . 3.4. wall i n t e r f e r e n c e c o r r e c t i o n s 0 0 NO Q yes
included?
6 . 3. 5. c o r r e c t i o n s f o r model deflection NO
6. 3.6. Empty t e s t section calibration Yes
taken into account?
6. 3.8. additional r e m a r k s No special notation i s used to identify c o r r e c t e d
and uncorrected data.
6.4. W e r e t e s t s c a r r i e d out in different See 2.1. of this questionnaire and Table 3. 3
facilities on the c u r r e n t aerofoil?
If so, what facilities. A r e data A comparison of ARA and DFVLR-TWB p r e s s u r e
included in the p r e s e n t data b a s e ? distributions i s given in Figure 3. 7
6. 5. T o be contacted for f u r t h e r @ W. Puffert
information on t e s t s DFVLR
D-3300 Braunschweig
Q T . E . B . Bateman
A i r c r a f t R e s e a r c h Association (ARA)
Manton L a n e
Bedford, MK41 7 P F
England
@ E . Stanewsky
DFVLR-AVA
BunsenstraDe 1 0
D-3400 G6ttingen
7. References
[ I ] KijHL. P. The design of airfoils for t r a n s p o r t a i r c r a f t with improved high speed
ZIMMER, H. characteristics
DORNIER GmbH, Report 74/16B, 1974
[2] STANEWSKY, E . Development and wind tunnel t e s t s of t h r e e s u p e r c r i t i c a l airfoils f o r
ZIMMER, H. transport aircraft.
Z. Flugwiss. 23 (1975), Heft 718
[3] STANEWSKY, E . The DFVLR Transonic Wind Tunnel Braunschweig: Calibration r e s u l t s
P U F F E R T , W. f o r the modified t e s t section and r e s u l t s f o r the airfoil CAST 7.
M ~ L E R ,R. DFVLR Report I B 151-77/10, 1977
[4] HAMMOND, B. F . L . Some notes on model testing in the ARA two-dimensional facility.
A i r c r a f t R e s e a r c h Association Memo No. 170, 1975
[5] HAMMOND, B . F . L . ARA model t e s t note T 2814,
A i r c r a f t Research Association, Bedford
[6] SASMAN, P.K. Compressible turbulent boundary l a y e r with p r e s s u r e gradient and
CRESCI, R . J . heat t r a n s f e r .
AIAA Journal, Vol.4, No.1. January 1966, pp 19-25
8. L i s t of symbols
b span, tunnel width Relations used in the reduction of the boundary
C. I, L model chord layerddata
C
P
p r e s s u r e coefficient 6 = 1 - .L
u
) .d z
C
P
* p r e s s u r e coefficient a t M
6
e e
L
C~ Lift coefficient u
U
pitching moment coefficient e e
(based on 0.25 c )
d r a g coefficient H = 6*/0
'w' 'D
M, Ma. Mm f r e e s t r e a m Mach number c = (0.246
f
. e (-1. 561 . Hi) . Reo -0.268
) I
ML local Mach number (airfoil
surface, f ( p / po ) )
MB tocal Mach number (boundar
layer, f ( p g / p T ) )
H, h tunnel height. shape factor
P static pressure
Po. H f r e e s t r e a m total p r e s s u r e
P~ total p r e s s u r e in the
boundary l a y e r
Assumptions: P = 1
Re, R , E-6* RE Reynolds number. based on
f r e e s t r e a m conditions and TWITte = 1
chord length
nose radius Tw Wall t e m p e r a t u r e
f r e e s t r e a m total temperatur total t e m p e r a t u r e a t edge of
Tte
velocity in the boundary boundary l a y e r ( T
t e = To)
layer
maximum thickness
coordinates (Figure 3 . 1) Subscripts
( Z i s in the c a s e of the m f r e e s t r e a m conditions
boundary l a y e r m e a s u r e -
ments taken n o r m a l to the TE trailing edge
airfoil surface) u upper s u r f a c e
(I angle of attack 1 lower s u r f a c e
6 , DEL boundary l a y e r thickness e,E edge of boundary l a y e r
(u/ue= 0.99)
B boundary l a y e r
6*. DEL' displacement thickness
O, THETA momentum thickness
Y r a t i o of specific heats
T a b l e 3. 1 C o o r d i n a t e s of t h e a i r f o i l CAST 7 T a b l e 3 . 2 Design p r e s s u r e
a . Model: SP 120 (TWB t e s t s ) , , distribution
Pressure distribution at (x, + -)
Rs ; 6 . l o 6 Boundary layer: turbulent
Mm = 0.760 0 = 0.0
CL
CD
= 0.573
0.00458
C,,,
C
=
P
.
-0.L3551
34.5587
0.07580
0.12895 0 . 12695
0 . 24141 0.21113
0.48221 0.46230
0.70025 0.70051
OBZ820 OS289Y
1. ,3835 I . 14076
0.9123< 0.111(8
0.53289 0.55421
0.35108 0.43495
0 . 20055 0.36309
0.00269 (I. Z i S i l
-0.21<08 0 . I8454
-0.43112 0 . l0ZOI
-0.61032 0.03930
-0.75132 -0 OZSBI
-0820SB -0.09221
-0.88111 - 0 . 19051
-0.81114 -0.32130
-0.90171 -058Sil
-D.LlSlBB -0.39120
-0.88738 -0.32921
-0.88810 -0.23556
-07B102 -0. lZB.0
manufactured airfoil s e e F i g . 3. 1 -0.83271 -0.01747
-0.61581 0.09305
-0.5276% 0.19929
-0.98832 0.29211
-0.21118 0.36020
-0.10430 0.39117
-0.00889 0.39357
0.01860 0.51830
0.19893 0.31661
0.2U143 0.32913
0.29324 0 . 29385
b. Model: C P 7 (ARA t e s t s ) 0, tisol 0.17118
0.10612 OLOSBB
0.00021 0.06(101
Upper Surface (mml Lower surface (mm) 0.038~8 0.03585
O.OLi85 0 Dl785
x/c x [mm) ~esisn ~ c t u l l ~rror I*#isn AcCu.1 Zrror
E x p e r i m e n t ARA: T a b l e 3 . 5 and F i g u r e 3 . 2
0.115 14.605 6.114 6.739 +O.OOS -1.468 4 9 r0.028
Experiment DFVLR-TWB: Figure 3 . 2
0.155 19.685 7 . 6 7.36 0 -5.131 -1.156 +0.025
0.215 27.305 8.016 7.998 -0.018 -5.883 8 9 tO.010
0.275 34.925 8.402 8.379 -0.023 -6.304 -6.312 rO.0011
0.335 42.545 8.618 8.603 -0.OlS -6.383 -6.383 0
-The location o f t h e p r e s s u r e o r i f i c e s
0.395 50.161 8.700 8.694 - 0 . ~ 6 -6.142 -6.137 -0.00s i s given with t h e s u r f a c e p r e s s u r e
0.655 57.785 8.656 8,651 - 0 . ~ 5 -5.626 -5.618 -0.008 d i s t r i b u t i o n s in T a b l e s 3. 4 . 3 . 5 and
0.515 65.405 8.479 8.476 -0.003
3. 6 and in F i g u r e 3 . 1
-4.895 -6.1179 -0.016
0.515 73.025 8.1U 8.146 0 -4.W3 -3.980 -0.021
0.635 80.615 7.630 7.628 -0.W2 -3.010 - 2 . 8 -0,025
0.695 88.265 6.886 6.891 rO.Ws -1.989 -1.9111 -0.03I
0.755 95.885 5.890 5.883 -0.007 -1.026 -0.99l -0.035
0.815 103.125 1.651 4.64, -0.010 -0.264 -0.221 -0.043
0.875 111.125 3.226 1.121 -0,005 0.132 0.168 -0.036 l.O,04%C 1
+0.05
0.920 116.840 2.096 1.088 -0.008 0.099 0.117 -0.018 AZmm %
.-
0.950 120.650 0.336 1.114 O -0.079 -0.081 +0.002
0
--__ ,:
0.978 12h.111 0.627 0.621 -0.002 -0.113 5 6 rO.023
\ -.-..--._ -LA'. 101* (127mmJ
I.WO 127.000 0.043 0.038 -0.005 -0.589 -0.599 tO.Ol0
-0.05
--.._,,.'
I-ao4-1.6
- u1s
---US
LI.di* edge in.p.ered by *eru,ir. ceq1.c.. ."d Sh.dorgr.ph r.eh.ique.
kccuracp: +0.007 m
ARA CAST 7 a i r f o i l (Model C P 7 )
M e a s u r e d e r r o r s of m a n u f a c t u r e d a i r f o i l
Table 3 . 3 Flow conditions included in present data s e t
Transition .068&
in 7 *
7/7L means: Roughness band of . 0 6 mm diameter glass spheres
c 0" upper and lover surface.
I' Corrected angles of attack " Compared fo design presaure distribution (Figure 3 . 21
~ ~ 3 . 4b D Fl m R ~ - T W B tests. Aerodynamic coefficients, airfoil surface and top and bottom wall
p r e s s u r e distributions
Transition at 7 $ c on upper and lower surface. b. Airfoil s u r f a c e and top and bottom wall
a. Aerodynamic coefficients pressures
E: The upper surface and top wall p r e s s u r e s
a r e L.t-
"I. *LC* E-WRI &PIU MR. MACW K-6.RS U P U
NR. PSACli E-6.RE &PHA CA C* CY
n ,763 5.9, -1.1. U S .T~P 5.96 ..I
2493 .6PI 5.88 -2.m -.I8867 ,889632
BIP5 ,761 6.86 -1.88 ,1478 -.I1858 .8893Ul
24'16 .783 5.PB .88 -.I1876 .Be95511
x n CP XVIL SPI XIL ' CP x m cpv
e491 .let 5.97 >.Be ,5482 -.a1877 .BIB416
2498
2499
,781
,782
5.94
5.96
2.88
3.m
. ~ B S B -.he979
.P857 - . 1 1 3 6 9
.BLP~W
.821677
.**a
.**a
1.aa9s
.age.
- 5 . ~ 5
-4.5 -..
-...I*
.76
.eee
.*a4
1...
1.13,~
.I756
.S110
-..PI
-4.5,
-1.15
-..em
-.IS58
-.##as
8588
8581
25BP
+699
,788
+6PP
5.95
5.9,
5.98
I.aB
4.58
5.BB
1.8617
1.8297
1.8187
-.12588
-.,I691
-.11898
,839835
1868949 .*I5
..sS
.*a
.6SP5
.a816
.I1SP
-.IS96
-3.16
-3.B.
-8.9s
-I.%#
-...47
-.I.1@
.@.st
.IIW
..I$
..SI
..U
.DIP7
-.em9
-.SSP1
-3.a.
-..DS
-1.5.
..
..S4
$I
.SM -.a651 -1.85 .1118 ..W -.a#.. -I..% ..I69
PIP@ .761 5.98 -1.BB .I867 -.I1769 .818196 .@a* 7 -1.m .1181 .we -.85%8 -1.I. .#.I P
.I*. -.S491 -.75 ...St
ma4
ell85 9
5.9,
5.98
-1.88
.88
. 2 6 ~ -~. l l e m
.a268 -.19195
.a!e~ax
.811441
.I.* U S -.5* - .I-
-.S111
-.1661
-.11
-.51
-..as2
-..IIs
P486 .?bl 6.BI .58 .St611 -.IPP)P .BLLllb .I@@ 7 3 -.D5 -.#Oat -.6658 -.*5 -.,4S7
PIP! ,768 5.99 .75 ,5789 -.IPSPI .BIIBJ@
3 .11 -.a556 .Pa. -.1871 .#a -.me16
9487 .168 5.92 1.88 ,6897 -.1311a .813658 .PM -.I838 .PI -.IPse .sM -.81%0 . ~ 5 -.1518
2488 ,759 6.88 1.58 ,7187 -.I4ISP .BIPPIB .lo. .S1 -.llsl .3.. -..a14 .%I -.I,#&
BILIP ,768 5.94 2.88 ,7258 -.I1538 +841963 .3U -.55P8 .11 -.lee1 .JU -..I., .11 -.1.11
.lo1 -.SM1 I... .18@ -.6188 I... -.I1PI
21198 ,761 5.99 3.W ,7384 -.I2548 ,861552 .a** 1.95 -.@109
-.ST13 .as* -..a11 1.95 -.!Is$
-.5S.@ 1.5 -..Tee ...I -.66$P 1.5, -.#SSP
2511 ..a1 5.m .58 . J @ I e -.B*BBI +a89738 .5SO -.5985 8.75 -.IS11 -.6636 1.15 -.a648
4 -.65.5 D.IO -..a87 -.6911 9.I. -..539
25x2 +4PP 5.76 .58 .1$91 -.8P495 .8@8745 -.UP5 P.91 -..,Pa
2514 ,682 5.86 +5B .a812 -.IBEBB .BBIIP73 -.711P 8.81 -.#a66
.6PI -.6546 0.5s -.IJPe -.la93 9.5. -.#a43
~ 5 1 5 ,658 5.8 .58 ,4448 -.>a659 .Rae466 .m. - 3 9.75 -.I393 .?I# -.53Ps 0.71 -..a18
P516 .782 5.88 .58 .a674 -+11916 .81@!74 .SIB -.PSPO 1.58 -.IS99 8 -.9981 3.5. -..3.9
P517 ,717 5.81 .58 .4Sa1 -.I1458 .8a99(13
2518 .11P 5.81 .$a .a965 -.I1114 .IIeJ$P -..64. -5.25
-4.58
-.II1# -.1611 -5.85 -.a811
.wee -.tetm .*nnana
.9S .I359 -.@IS8 .95. ..Jea -4.m -...a6
DSLP
e5ea
,751
.75P
5.96
5.97 .
.SB
.5PSB -.18JS5 .81@711
.915
I...*
.#I40
.,IS9
-1.15
-
I
.
.Ian8
.em4
7
1.111
.lMl
.Wll
-1.15
-3.m
.e161
.Be96
8524
D581
.765
.7,8
5.88
5.99
.58
.5e
.SDIO
.,ale
-.IB1.8
-.,33e3
.*Ill91
.#IPB@7
.erne t.mes -e.zs .e111 .am 1.1119 -9.95 .e,6e
.*I4 -.I818 -1.58 .el119 4 .Is96 -I.$. .a
PSBP .,re 5.s~ .$B .s,.e - . I J ~ & .~1639a .ems -.UEB -1.~5 ..IBP .#I. -.~P.s -I.P, .eee,
9523 .se! 5.92 .5a -.13ma .neeme .#PI -.a556 -I.BI ..PPI ,191 -.16.. -1.e. .eJI.
.*S -.I966 -.75 .BlsP -.as42 -.75 .e118
I -.3151 -.5@ ! -.I726 - 5 .eJSO
P581 .1%9 4 . 1 .58 .S161 -.IPB5I .0IP171 -.amas .wae
~ $ 8 5 .761 5.18 .sB .5PP8 -.IPS49 .811555
.IS* -.95 . ~ s s -.nres -.PS .a116
.as. -.5113 .em -.we3 .en. -.ma6 .ee .aa.~
P586 .168 5.81 .58 -.lSJaD .*IBS99 .D50 -.6Pll .95 -.a111 -.a686
. .P5 .IS.$
~SBI .,6, 7.85 .5e .%,PI -.tea52 .e1@5se .ISe -.555@ .58 -.llPO .3W - 4 .% .,PI6
PSBB .we ~e.m .sap6 - . I ~ P D ~. a e e e e ~ .a51 -.3376 .15 -...*I .aIB -.a861 .1S .ID65
9589 .758 tI.77 .58 .54111 -.le9*4 +0183P* .IS# -.I371 1.8. .1113
2518 ,768 13.41 .58 -.I1991 .IIIIP4 .55* -.!165 I.sl .IJI.
.6M .a454 I.P, 8 .6S. ..688 1.PS .1588
.lW 9 1.5. .#I96 .731 .PIS1 t . 3 .a879
.a50 .DPeI 7 .816S .851 3 L.7, .It91
2525 ,768 4.89 8.m .11!6 -.IJI9P .a48354 1.9.e .III9 P.ll 11113 P.es
e5Pb
8587
e53i
.
.768
,762
.
5.83
7.8,
2.m
n.sa
8.~31
.1Pl9
.raar
.,a88
-.11$5S
-.139&6
-.I,PJ6
.eJIIY)*
.e1sI99
.a39436
*.E5
e.sa
-.Be79
-.ears
1.111 .B9m
s.P5
2.3s
.It*.
-.111.
- . ~ s P
OSJB ,759 9.96 2.m .IT,* -.la711 .I31793 2.75 -..a47 9.15 -.@I**
1.58 -.Be19 1.W .a146
2589 ,758 il.78 P.@@ .7116 -.I4793 .#3e559
95~8 ,759 13.49 2.m .,.)re -.I4957 .13lSbl
L model chord
xwlocation of wall orifices(with r e f e r e n c e t o model
cp a i r f o i l surface p r e s s u r e coefficients leading edge)
C P W wall p r e s s u r e coefficient
Table 3 . 4 Continued
NR. MACH i--RE ALP- NR. MACH I-6.RI ALPHA
8 7 1761 5.9s I... 4 .759 6.l. ,.%a
XYIL CPY
I CP XYIL CP"
YR. IaCII E-6.RZ LPHL MI. MhCH =-LIRE LPIU NR. MACH L-6.RE LPHA
EN. 6 1.9s -e.a. east .76. 1.99 .IS *~PB .,el 5.99
x n CP XI& CPI XA CP xwn CPW x n CP XYIL CPY
