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 (CL), Air Density (ρ), Aircraft Gross Wing Area (S) & Fluid Velocity (uFluid) 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
.