Lift From Prandtl’s Lifting-Line Theory Calculator

Lift is the force generated by an airfoil (such as a wing) as it moves through a fluid (typically air). Lift is generated by the pressure difference between the upper and lower surfaces of an airfoil. Prandtl’s Lifting-Line Theory explains the lift distribution along a finite wing, incorporating the impact of circulation. It is especially relevant for low aspect ratio wings, contributing to our overall understanding of aviation aerodynamics. The formula to calculate Lift From Prandtl’s Lifting-Line Theory as follows:

Where:

• $L$: Lift force generated by an airfoil or a wing.
• $\rho$: Air density, representing the mass of air per unit volume.
• $V$: Airspeed or velocity of the air flowing over the wing.
• Γ: Circulation, which is a measure of the strength of the vortices around the wing. It is related to the lift distribution along the span of the wing.