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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

 

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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 low-speed wind tunnel at standard sea-level conditions we must have,

  • Flow Velocity in test section in feet/sec (ft/s)

  • Pressure at a point on the airfoil (lb/ft^2)

  • and if the flow velocity is increased such that the free stream Mach number becomes value.

The formula used for Pressure coefficient at a point on the wing is Cp = Cp0/ squareroot (1-Mach(infinity)^2)

 

Download Free Program to Calculate the Pressure Coefficient Cp at a point on an Airfoil or wing

 

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