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This project will be discussing one method of evaluating the potential flow (Ideal flow) over 3 airfoils; NACA 0006, NACA 0012, NACA 0018. Computing the Coefficient of lift of the airfoil at 0 angle of attack and the surface velocities at different distances from the leading edge using the Source/Vortex Panel Method and validating it using XFOIL.
Ahmed-Mohamed-Hassan-Abdulrahman/Source-Vortex-Panel-Method-Potential-Flow-implementation
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This project will be discussing one method of evaluating the potential flow (Ideal flow) over 3 airfoils; NACA 0006, NACA 0012, NACA 0018. Computing the Coefficient of lift of the airfoil at 0 angle of attack and the surface velocities at different distances from the leading edge using the Source/Vortex Panel Method and validating it using XFOIL.
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