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AeroCFD_DZ_NACA4412
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0 Geometries 0 Meshes 0 Simulation setups 0 ResultsAbout this project
The goal of this project is to analyze the aerodynamic performance of a UAV wing section (NACA 4412 airfoil) using Computational Fluid Dynamics (CFD). The study will evaluate how pressure distribution, lift, and drag vary with angle of attack, and determine the stall characteristics and efficiency (L/D ratio).
