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 = 8and taper ratio = 0.8. Assume that δ = τ . Calculate the lift and induceddrag coefficients for this wing at a geometric angle of attack = 7◦.
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 = 8and taper ratio = 0.8. Assume that δ = τ . Calculate the lift and induceddrag coefficients for this wing at a geometric angle of attack = 7◦.
Principles of Heat Transfer (Activate Learning with these NEW titles from Engineering!)
8th Edition
ISBN:9781305387102
Author:Kreith, Frank; Manglik, Raj M.
Publisher:Kreith, Frank; Manglik, Raj M.
Chapter5: Analysis Of Convection Heat Transfer
Section: Chapter Questions
Problem 5.55P
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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 = 0.8. Assume that δ = τ . Calculate the lift and induced
drag coefficients for this wing at a geometric angle of attack = 7◦.
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