Calculate CL Lift Coefficient of Airplane

 Method for Calculating the Lift Coefficient of an Airplane Flying at Standard Sea-level

• Calculate Lift about the quarter chord point per unit span

• Calculate Drag about the quarter chord point per unit span

• Calculate Moment about the quarter chord point per unit span

• Calculate Pressure Coefficient at a Point on Wing and Airfoil

• Calculate Induced Drag Coefficient and Induced Drag

• Calculate Total Drag

• Calculate Cl and Cd

• Calculate Lift Coefficient for Airplane

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Lift Coefficient CL of an Airplane

To calculate the Lift coefficient of an Airplane flying at standard sea-level conditions, we must have the value of the Wing area in feet ^2.

The amount of the Lift that the airplane is generating in pounds lb.

The flight Velocity of the Airplane in miles / hr (mi/h)

Performing the calculation, the Dynamic Pressure is computed and the value of Lift Coefficient of the Airplane is computed.

Download Free Program to Calculate the CL Lift Coefficient of an Airplane