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Airfoil pressure distributionI 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. |

HiQuote:
Thank u a lot 1ce again.. |

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