The maximum angle of climb for a turbojet powered aircraft is 8.97°.
Let us consider the velocity is steady.
T is thrust, W is weight, L for lift force, D for drag and θ is angle of climb
From the given information, we can write the below equations,
T = D + W sinθ -----(1)
L = W cosθ -----(2)
Given that, L/D = 10.5
D = L/10.5 -----(3)
Placing (3) in (1), we have
T = L/10.5 + W sinθ
T = (W cosθ)/10.5 + W sinθ
cosθ + 10.5 sinθ = T/W * 10.5
cosθ + 10.5 sinθ = (2000/8000) * 10.5
cosθ + 10.5 sinθ = 2.625
Solving the above equation, we get θ = 8.97°
Thus, the maximum angle of climb is 8.97°.
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