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Engineering, 11.07.2019 01:30 gonsalex6688
Consider a wing with a thin airfoil section (naca 2410) at 7 deg. angle of attack with chord and span are 0.8 and 5 m, respectively. calculate the lift coefficient, moment coefficient around the leading edge, and induced drag coefficient if the correction factor is 0.98.
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Consider a wing with a thin airfoil section (naca 2410) at 7 deg. angle of attack with chord and spa...
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