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Calculate Cp Pressure Coefficient at a Point on Wing and Airfoil Method to Calculate the Pressure Coefficient Cpat a Point on the Wing and Airfoil 

Aerospace



Pressure Coefficient Cp at a Point on Wing and Airfoil To calculate the Pressure Coefficient Cp value at a point on the wing we must know the value of the altitude at which the airplane is flying in meters. 

We also need to know the pressure at a point on the wing of the airplane in N/m^2
And the value of Airplane Velocity in m/s.
Performing the Calculation we have the following parameters,
The value of Density at given altitude. The value of Dynamic pressure q = 1/2 * density * velocity^2
and the Value of the Pressure Coefficient Cp Cp = (p  p(infinity))/ q (infinity)


In order to calculate the pressure Coefficient Cp value at a point on the airfoil placed in a lowspeed wind tunnel at standard sealevel conditions we must have,
The formula used for Pressure coefficient at a point on the wing is Cp = Cp0/ squareroot (1Mach(infinity)^2)
Download Free Program to Calculate the Pressure Coefficient Cp at a point on an Airfoil or wing
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