Calculate Lift about the Quarter-Chord Point Per Unit Span

 Method to Calculate the Lift about the Quarter Chord point per Unit Span with Constant Chord Wing Placed in Low-Speed Wind Tunnel

• 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 about the Quarter-Chord Point of Constant Chord Wing

In order to calculate the lift about the quarter chord point per unit span of a constant chord wing placed in a low-speed wind tunnel.

We must first have the value of the Wing Chord length (c) in meters.

We must also have the Flow velocity in the test section in meter/second.

The Angle of Attack of the Airfoil and the Lift Coefficient corresponding to that given AOA.

Also, the Value of the Moment Coefficient about the quarter-chord point is also required for the given angle of attack.

The value of meu = 1.789e-5 kg/ms is taken. The value of the Reynold's Number is entered.

Performing the Calculation, the value of the dynamic pressure is calculated and the value of Lift about the quarter chord point is calculated.

The formula for Lift is Lift = L = qSCl, where q = Dynamic Pressure, S = Wing Area, Cl = Wing Lift Coefficient.

Download Free Program to Calculate the Lift about the Quarter-chord Point per Unit Span