Question

Determine the coefficient of lift given the following information. A Gulfstream G280 has a wing area of 46 m^2. Its total mass during a particular flight is 13,500 kg at its current altitude is 0.28 kg/m^3 and is cruising at 840 km/hr. The air density is _______.

a) The question is incomplete.
b) 0.028 kg/m^3
c) 0.28 kg/m^3
d) 2.8 kg/m^3

Answer 1

The coefficient of lift can be determined using the formula: coefficient of lift = Lift / (0.5 * density * velocity^2 * wing area). Given the wing area of the Gulfstream G280 is 46 m^2 and the total mass is 13,500 kg, we need to find the air density at the current altitude.

Step-by-step explanation:

The coefficient of lift can be determined using the formula: coefficient of lift = Lift / (0.5 * density * velocity^2 * wing area)

Given the wing area of the Gulfstream G280 is 46 m^2 and the total mass is 13,500 kg, we need to find the air density at the current altitude.

Since the question is incomplete and does not provide the air density, option (a) is the correct answer.