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NACA 0012 Aerodynamic Characterization & CFD Validation
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1 Geometry 5 Meshes 1 Simulation setup 1 ResultAbout this project
High-fidelity steady-state incompressible flow analysis over a NACA 0012 symmetric airfoil. The study focuses on quantifying lift and drag coefficients ($C_L$, $C_D$) and visualizing pressure distribution ($C_p$) at varying angles of attack (AoA). Validated against experimental NASA Langley wind tunnel data.
