5.2 Consider the following aircraft flying in straight and level unacceleratedtrimmed flight at M 0.2 at sea level.MAC12 ftXegWXcg0.5cwingMacailMacit= -5000 ft lb= 0ac wingT = 3000 lbW = 12,000 lbCtail =4 ftbwing = 30 ftCwing = 8 ft(a) Find the lift of the wing and the lift of the tail. Assume Lwing andLtail 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?

Answered: Image /qna-images/answer/0ccdacac-e23b-4a20-8c1c-d3d88fec13f5.jpg

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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