An airplane is cruising at a velocity of 800 km/h in air whose density is 0.526 . The airplane has a wing planform area of 90 . The lift and drag coefficients on cruising conditions are estimated to be 2.0 and 0.06, respectively. The power that needs to be supplied to provide enough trust to overcome wing drag is

(a) 9760 kW
(b) 11,300 kW
(c) 15,600 kW
(d) 18,200 kW
(e) 22,600 kW

Complete question:

An airplane is cruising at a velocity of 800 km/h in air whose density is 0.526 kg/m³ . The airplane has a wing planform area of 90 m² . The lift and drag coefficients on cruising conditions are estimated to be 2.0 and 0.06, respectively. The power that needs to be supplied to provide enough trust to overcome wing drag is

The power that needs to be supplied to provide enough trust to overcome wing drag is 15,600 kW.

(C) 15,600 kW

Explanation:

Given;

velocity of the airplane, v =  800 km/h = 222.22 m/s

density of air, ρ = 0.526 kg/m³

wing planform area, A = 90 m²

lift coefficients, CL = 2.0

drag coefficients, CD = 0.06

Power supplied = FD* V

This is approximately 15,600 kW.

Therefore, The power that needs to be supplied to provide enough trust to overcome wing drag is 15,600 kW.

The correct option is C

answer:

2d

explanation: