Question

Which of the following is the correct formula for lift of an aircraft?

(a) L=\(\frac{1}{2}\)ρV^2SCl

(b) L=\(\frac{1}{2}\)V^2SCl

(c) L=\(\frac{1}{2}\)ρV^2Cl

(d) L=\(\frac{1}{2}\)PV^2SCl

I have been asked this question during an online exam.

Question is from Lift Force in portion Aircraft Force Systems and the Equations of Motion of Aircraft Performance

Answer 1

The correct option is (a) L=\(\frac{1}{2}\)ρV^2SCl

Explanation: The correct formula for lift of an aircraft is L=\(\frac{1}{2}\)ρV^2SCl where L is lift, ρ is density, V stands for velocity of the aircraft, S is span and Cl is coefficient of lift. Lift is one of the fundamental aerodynamic force that is caused for the upward movement of the aircraft.