MAE305_pset06

# MAE305_pset06 - the spanwise eﬃciency factor is e ` = 0...

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Problem Set 6 Fa 2009 Due Thursday, November 5, 2009 1. An airplane has a wing planform area of S =60m 2 , a wing span of b =24m ,and a gross mass of M =25 , 000 kg. It is in level, unaccelerated ﬂight, which implies L = Mg at a true airspeed of V = 225 m/s, a density altitude h d =12 , 500 m, at an air temperature T = 227 K. (a) What is the value of the lift coeﬃcient under these conditions? (b) Assuming the spanwise eﬃciency factor is e =0 . 95, what is the induced drag? What is the ratio of lift to induced drag? 2. An airplane with a wing area of S = 450 ft 2 and a wing span of b =70ftisﬂy ingat a pressure altitude of h p =8 , 000 ft at a true airspeed of V = 280 mph. The ambient air temperature is T = 500 R. The wing has zero camber and an absolute angle of
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Unformatted text preview: the spanwise eﬃciency factor is e ` = 0 . 98. For these conditions (a) What is the total lift generated by the wing (in pounds force)? (b) What is the parasite drag 1 (in pounds force) if the parasite drag coeﬃcient has the constant value (independent of angle of attack) of C D p = 0 . 0190? (c) What is the value of the induced drag coeﬃcient? (d) What is the total drag force (in pounds)? (e) What is the ratio of lift to (total) drag? 3. Problem 5.34 in Anderson. 1 The total drag often is represented as the sum of the parasite drag D p and the induced drag D i , having corresponding drag coeﬃcients C D p and C D i such that D = D p + D i = 1 2 ρ ∞ V 2 ∞ S ( C D p + C D i ) ....
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