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NACA2412_Transonic_CFD
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0 Geometries 0 Meshes 0 Simulation setups 0 ResultsAbout this project
Study aerodynamic behaviour (CL, CD, CP) of NACA 2412 from 0° to 18° AoA Capture flow separation, stall onset, and shock wave formation at Mach 0.7–0.8 Validate results against NACA experimental data from Tech Report archives
