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Double Wedge Airfoil in Supersonic Flow

This code provides coefficient of section lift, drag and moment of double wedge aerofoil.
(181 downloads for this version - 181 downloads for all versions)
Vijay Gopal
Vijay Gopal
Supported Scilab Version
Creation Date
November 23, 2015
            This code provides the variation of CL, CD and CM with angle of attack of a
symmetrical double wedge airfoil. Additionally it provides the coefficient of
pressure variation at a requested angle of attack on the surface of the airfoil.
The user can provide the geometry and free stream condition to carryout
Files (1)
[14.70 kB]
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