__Lift Force Calculator:__

__Lift Force Calculator:__

Enter the values of coefficient of lift, C_{l}, area, A_{(m2)}, air density, d_{(kg/m3)} and velocity, V_{(m/s) } to determine the value of lift force, F_{l(N)}.

__Lift Force Formula:__

__Lift Force Formula:__

The lift force formula is fundamental in aerodynamics, used to calculate the force that allows an object, such as an airplane wing, to rise and stay in the air.

Lift force, F_{l(N)} in Newton is calculated by dividing the product of coefficient of lift, C_{l}, area, A_{(m2)} in square metres, air density, d_{(kg/m3)} in kilogram per cubic metre and velocity, V_{(m/s)} in metre per second by 2.

Lift force, F_{l(N)} = C_{l} * A_{(m2)} * ( d_{(kg/m3)} * V^{2}_{(m/s)} ) / 2

F_{l(N)} = lift force in Newton, N.

C_{l} = coefficient of lift.

A_{(m2)} = area in metres, m.

d_{(kg/m3)} = air density in kilogram per cubic metre, kg/m^{3}.

V_{(m/s)} = velocity in metre per second, m/s.

__Lift Force Calculation:__

__Lift Force Calculation:__

1. Calculate the lift force on an airplane wing with a coefficient of lift of 0.5, a wing area of 50 m², air density at altitude is 1.225 kg/m³, and the velocity is 250 m/s.

Given: C_{l} = 0.5, A_{(m2)} = 50m^{2}, d_{(kg/m3)} = 1.225kg/m^{3}, V_{(m/s)} = 250m/s.

Lift force, F_{l(N)} = C_{l} * A_{(m2)} * ( d_{(kg/m3)} * V^{2}_{(m/s)} ) / 2

F_{l(N)} = 0.5 * 50 * ( 1.225 * 250^{2} ) / 2

F_{l(N)} = 953906.25N.

2. Given: C_{l} = 1.2, F_{l(N)} = 1500N, d_{(kg/m3)} = 1.225kg/m^{3}, V_{(m/s)} = 50m/s.

Lift force, F_{l(N)} = C_{l} * A_{(m2)} * ( d_{(kg/m3)} * V^{2}_{(m/s)} ) / 2

A_{(m2)} = F_{l(N)} / ( d(kg/m^{3}) * V^{2}_{(m/s) })/ 2 * C_{l}

A_{(m2)} = 1500 / (1.225 * 50 ) / 2 * 1.2

A_{(m2)} = 0.816m^{2}.

__Lift Force:__

__Lift Force:__