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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- Fall '08
- Aerodynamics, Lift, ambient air temperature, Lift curve slope, spanwise eﬃciency factor