If the wing is at a 6° angle of attack, calculate CL and CD.

1. For the Cessna Cardinal in Prob. 5.21, calculate the induced drag when the velocity is 85.5 (stalling speed at sea level with flaps down). Prob. 5.21 The Cessna Cardinal, a single-engine light plane, has a wing with an area of 16.2 m2 and an aspect ratio of7.3l. Assume that the span efficiency factor is 0.62. If the airplane is flying at standard sea-level conditions with a velocity of 251 km/h, what is the induced drag when the total weight is 9800 N? 2. Consider a finite wing with an area and aspect ratio of21.5 m2 and 5, respectively (this is comparable to the wing on a Gates Learjet, a twin-jet executive transport). Assume that the wing has a NACA 65-210 airfoil, a span efficiency factor of 0.9, and a profile drag coefficient of0.004. If the wing is at a 6° angle of attack, calculate CL and CD.


 

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