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Calculate Drag about the QuarterChord Point per Unit Span Method to Calculate the Drag about the Quarter Chord point per Unit Span with Constant Chord Placed in LowSpeed Wind Tunnel 

Aerospace



Drag about the QuarterChord Point of Constant Chord Wing In order to calculate the drag about the quarter chord point per unit span of a constant chord wing placed in a lowspeed 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 quarterchord point is also required for the given angle of attack.
The value of meu = 1.789e5 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 Drag about the quarter chord point is calculated. The formula for Lift is Lift = D = qSCd, where q = Dynamic Pressure, S = Wing Area, Cl = Wing Drag Coefficient. The value of Lift to Drag Ratio L/D is also computed. Download Free Program to Calculate the Drag about the Quarter chord point per Unit Span

