How to Calculate The Modern Lift Equation?
The Modern Lift Equation calculator uses Lift on airfoil =
(Lift Coefficient*
Air Density*
Aircraft Gross Wing Area*
Fluid Velocity)/2
to calculate the Lift on airfoil, The Modern Lift Equation states that lift L is equal to the lift coefficient times the air-density times half of the velocity squared times the wing area. Lift on airfoil is denoted by L symbol.
How to calculate The Modern Lift Equation using this online calculator? To use this online calculator for The Modern Lift Equation, enter Lift Coefficient (C_{L}), Air Density (ρ), Aircraft Gross Wing Area (S) & Fluid Velocity (u_{Fluid}) and hit the calculate button. Here is how the The Modern Lift Equation calculation can be explained with given input values -> 144.12 =
(5*
1.201*
4*
12)/2
.