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0.20c simulated split flap deflected 60 R 6 x 10? Standard roughness, 6 x 10? Section lift coefficient, c? R 9.0 x 10? 6.0 3.0 Standard roughness 6.0 x 10? 0.20c simulated split flap deflected 60 R 6 x 10? Section angle of attack, ??, deg. NACA 0012 Wing Section Section drag coefficient, c? R 9.0 x 10? 6.0 3.0 Standard roughness 6.0 x 10? Moment coefficient, c??.?. R a.c. position x/c y/c 9.0 x 10? .250 0 6.0 .250 0 3.0 .250 0 Section lift coefficient, c? NACA 0012 Wing Section (Continued)

          0.20c simulated split
flap deflected 60
R
6 x 10?
Standard roughness,
6 x 10?
Section lift coefficient, c?
R
9.0 x 10?
6.0
3.0
Standard roughness
6.0 x 10?
0.20c simulated split
flap deflected 60
R
6 x 10?
Section angle of attack, ??, deg.
NACA 0012 Wing Section
Section drag coefficient, c?
R
9.0 x 10?
6.0
3.0
Standard roughness
6.0 x 10?
Moment coefficient, c??.?.
R
a.c. position
x/c y/c
9.0 x 10? .250 0
6.0 .250 0
3.0 .250 0
Section lift coefficient, c?
NACA 0012 Wing Section (Continued)

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0.20c simulated split
flap deflected 60
R
6 x 10?
Standard roughness,
6 x 10?
Section lift coefficient, c?
R
9.0 x 10?
6.0
3.0
Standard roughness
6.0 x 10?
0.20c simulated split
flap deflected 60
R
6 x 10?
Section angle of attack, ??, deg.
NACA 0012 Wing Section
Section drag coefficient, c?
R
9.0 x 10?
6.0
3.0
Standard roughness
6.0 x 10?
Moment coefficient, c??.?.
R
a.c. position
x/c y/c
9.0 x 10? .250 0
6.0 .250 0
3.0 .250 0
Section lift coefficient, c?
NACA 0012 Wing Section (Continued)

Added by Michelle H.

University Physics with Modern Physics

Hugh D. Young 14th Edition

Instant Answer

Solved by Expert Sri K

08/21/2023

Step 1

87 - Drag coefficient (Cd) = 0.020 We can calculate the area (A) of the airfoil as follows: A = c * l = 5 m * 5 m = 25 m^2 Show more…

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Calculate the lift and drag force on a NACA 0012 airfoil with standard roughness at Re=6 million operating at 9 degrees angle of attack in a relative wind of 10 m/s, with a chord of 5 meters and a length of 5 meters in a standard atmosphere. Use the theory of wing sections curves from PPT. Update: In the problem, the line corresponding to section drag coefficient curve originating from cl corresponding to 9 degrees does not intersect. You can estimate it to: CL = 0.87 Cd = 0.020 Angle of attack = 9 degrees Re = 6 million Chord = 1.5 m Length = 5 m Calculated area = From curves: CL = Cd = Lift = Drag =

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