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
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5.2 Consider the following aircraft flying in straight and level unaccelerated
trimmed flight at M 0.2 at sea level.
MAC
12 ft
Xeg
W
Xcg
0.5cwing
Macail
Macit
= -5000 ft lb
= 0
ac wing
T = 3000 lb
W = 12,000 lb
Ctail =4 ft
bwing = 30 ft
Cwing = 8 ft
(a) Find the lift of the wing and the lift of the tail. Assume Lwing 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?
Transcribed Image Text:5.2 Consider the following aircraft flying in straight and level unaccelerated trimmed flight at M 0.2 at sea level. MAC 12 ft Xeg W Xcg 0.5cwing Macail Macit = -5000 ft lb = 0 ac wing T = 3000 lb W = 12,000 lb Ctail =4 ft bwing = 30 ft Cwing = 8 ft (a) Find the lift of the wing and the lift of the tail. Assume Lwing 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?
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