Airfoil pressure distribution
I am given a project to transform an airfoil from a cylinder using joukowski transform. The cylinder is in zeta plane and the airfoil is in z plane. I did the plotting and i got the airfoil shape using matlab. but i want to know how to plot the pressure distribution over the airfoil.
The inputs to my program are:
Velocity, Angle of attack, coordinates of center of circle(zeta plane), radius of circle(zeta plane).
Can somebody please tell me how to plot pressure distribution for an airfoil?
See the book Aerodynamics by Milne Thompson, or any book of Aerodynamics from the 50's. Back they've used on daily bases conformal transforms for evaluating the Aerodynamics.
If I remember correctly the flow around a Jukowsky airfoil has a closed form solution, so your Cp should be a simple formula.
Thank u a lot 1ce again..
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