Engineering, 27.10.2021 07:20 hxmiltrxshh
The measured lift slope for the NACA 23012 airfoil is 0.1080 degree−1 , and αL=0 = −1.3 ◦ . Consider a finite wing using this airfoil with AR = 8 and taper ratio of 0.8 which corresponds to τ = 0.054 and e = 0.95. Calculate the lift and induced drag coefficients for this wing at a geometric angle of attack of 3◦ . CL ≈ 0.37 and CDi ≈ 0.006.
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The measured lift slope for the NACA 23012 airfoil is 0.1080 degree−1 , and αL=0 = −1.3 ◦ . Consider...
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