NACA 23015
A Model of wing section of type (NACA 23015) had been built to
be investigated and study the aerodynamic characteristics in a
subsonic wind tunnel at different angles of attack in order to
calculate the aerodynamic coefficients such as lift, drag, moment
and pressure coefficients. The effect of changing the angle of
attack on the aerodynamic coefficients was investigated. Then a
virtual model of the wing section and wind tunnel had been
programmed and tested by available standard packages such as the
(Design Foil) Program which uses Panel Method to calculate the
aerodynamic coefficients, and the finite element package (Ansys
Ver.9). A comparison was made to the arrived results with the
experimental data to check the accuracy of the results, and both
experimental and theoretical results were convergent. The
percentage of similarity between the experimental and theoretical
was 83% for the Aerodynamic characteristics.
Nomenclature CP Pressure coefficient -
AR Aspect ratio - CX Drag Coef. in x- Direction -
b Span mm CZ Lift Coef. in z- Direction -
c/a Mid thickness to radius D Drag N
ratio(thickness ratio) - H Local Pressure (heights
C The Chord of the Airfoil mm of Water column) mm
C D Drag coefficient - PU Pressure on the upper
CL Lift coefficient - L section surface mm
C M Moment coefficient - P LPressure on the lower
C MX Pitching Moment Coeff. section surface mm
in x – Direction - L Lift N
C MZ Pitching Moment Coef. M Moment on airfoil N.m
in z – Direction - P Pressure on airfoil N/m2
Table (1) The Coordinates of the wing section model -NACA23015
Table (2) The C PU of W.T. results at V = 36 m/s
Table (3) The C PL of W.T. results at V=36 m/s
Table (4) CL, CD, Cm at V=36 m/s for both Theoretical from
Design Foil and Experimental from W.T.
Experimental Investigation of Aerodynamic Characteristics of NACA 23015 under
different angles of attack and Comparison with Available Package
Figure (4) The relationship between the C PU & C PU ,for both theoretical and experimental and x/c
for α 0º,V = 36 m/s from Design Foil Program
Figure (5) The relationship between the C PU & C PL,for both theoretical and experimental and
x/c for α 6º, V = 36 m/s from Design Foil Program
Figure (6) The relationship between the C PU & C PL,for both theoretical and experimental
and x/c for α15, V = 36 m/s from Design Foil Program
Figure (7) The relationship between the C PU & C PL,for both theoretical and experimental and
x/c for 3º, V = 36 m/s from Design Foil Program
Figure (8) The relationship between the C PU &C PL, for both theoretical and experimental and
x/c for 9º, V = 36 m/s from Design Foil Program
Figure (9) The Pressure Coefficient Cp for both Figure (10) The Mach No. for both Tip & Tail of
Tip & Tail of the section at Angle of attack = 15° the section at Angle of attack = 15° & Velocity of
& Velocity of 36 m/s 36 m/s
Figure (11) The Pressure Coefficient Cp for Figure (12) The Mach No. for both Tip & Tail of
both Tip & Tail of the section at Angles of the section at Angles of attack = 0° & Velocity of
attack = 0° & Velocity of 36 m/s 36 m/
Figure (13) The Pressure Coefficient Cp Figure. (14) The Mach No. for both Tip
for both Tip & Tail of the section at & Tail of the section at angle of attack
Angles of attack = -9° & Velocity of 36 m/s = −9 ° & Velocity of 36 m/s
