An aircraft is in a steady level turn at a flight speed of 200 ft/s and a turn rate about the local vertical of 5 deg/s. Thrust frm the engine is along the flight direction. Given the weight of the aircraft as 50,000 lb and L/D of 10, determine the lift, drag and thrust required for the given equilibrium flight. Assume g = 32.2 ft/s

L = 4166.66 N and D = 46296.29 N and T = 96047.34 N

Explanation:

given,

flight speed = 200 ft/s

turn rate = 5 deg/s

weight of aircraft = 50000 lb

L/D = 10

for equilibrium in the horizontal position

w - L cos ∅ - D sin ∅ = 0 ... (1)

D cos ∅ - L sin ∅ = 0 ... (2)

L/D = tan ∅ = 10

∅ = 84.29°

50000 - L cos 84.29° - D sin 84.29° = 0

D cos 84.29° - L sin 84.29° = 0

on solving the above equation we get

L = 4166.66 N and D = 46296.29 N

thrust force calculation:

T = W sin ∅ + D

= 50000*sin 84.29 + 46296.29

T = 96047.34 N