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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