Question

An aircraft is climbing with a 20° of climb angle and a 5° of angle of attack having a mass of 11,000 kg and aircraft drag is 9,000 N then determine engine thrust.

(a) 5257.79 N

(b) 1810.97 N

(c) 28013.99 N

(d) 46082.75 N

The question was posed to me in examination.

I want to ask this question from Cruising Performance topic in section Cruising Performance of Aircraft Performance

Answer 1

The correct answer is (d) 46082.75 N

The explanation: Aircraft weight=mg=11000*9.81=107910 N.

Engine thrust: From equating the horizontal forces we get the following equation: T cos α=D+Wsin γ

T=\(\frac{D+Wsin\gamma}{cos\alpha}\)=\(\frac{9000+107910*sin(20)}{cos(5)}\)

T=46082.75 N.