WorldofAerospace.googlepages.com Contact Us | Sitemap | Home 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 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 .