5.2 Consider the following aircraft flying in straight and level unaccelerated trimmed flight at M = 0.2 at sea level. MAC 12 ft Xcg W Xeg = 0.5cwing = 0 acail Mac. = -5000 ft lb T = 3000 lb W = 12,000 lb %3D Cwing = 8 ft Ctail = 4 ft bwing = 30 ft (a) Find the lift of the wing and the lift of the tail. Assume Lwine and Ltail act at the quarter chord points. (b) Find the aircraft drag. (c) Assuming a rectangular wing, what is the total aircraft C? (d) What is the pitching moment coefficient for the entire aircraft?
5.2 Consider the following aircraft flying in straight and level unaccelerated trimmed flight at M = 0.2 at sea level. MAC 12 ft Xcg W Xeg = 0.5cwing = 0 acail Mac. = -5000 ft lb T = 3000 lb W = 12,000 lb %3D Cwing = 8 ft Ctail = 4 ft bwing = 30 ft (a) Find the lift of the wing and the lift of the tail. Assume Lwine and Ltail act at the quarter chord points. (b) Find the aircraft drag. (c) Assuming a rectangular wing, what is the total aircraft C? (d) What is the pitching moment coefficient for the entire aircraft?
Elements Of Electromagnetics
7th Edition
ISBN:9780190698614
Author:Sadiku, Matthew N. O.
Publisher:Sadiku, Matthew N. O.
ChapterMA: Math Assessment
Section: Chapter Questions
Problem 1.1MA
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