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Karan Ahluwalia
Independent Researcher
India
Abstract
This study presents a comparative evaluation of the aerodynamic performance of three representative NACA airfoil profiles—NACA 0012, NACA 4412, and NACA 2415—using low-turbulence wind tunnel testing and complementary numerical simulation. Experiments were conducted in a closed-circuit subsonic wind tunnel with a test section of 300 mm × 300 mm at Reynolds numbers ranging from 1×10^5 to 5×10^5. Lift and drag coefficients were measured at angles of attack from –4° to +16°, and uncertainty analysis was performed. A finite‐volume computational fluid dynamics (CFD) model was constructed using structured meshing and the Spalart–Allmaras turbulence model. Results show that NACA 4412 achieves the highest maximum lift coefficient (C_L,max = 1.52) but incurs greater drag at α > 10°, while NACA 0012 exhibits the lowest drag coefficient (C_D) across the tested range. Statistical analysis confirms significant differences in mean C_L and C_D values among profiles (p < 0.05). The combined experimental and simulation approach yields insights into optimum airfoil selection for low‐speed applications in UAV and small aircraft design.
KeyWords
Airfoil performance, Wind tunnel testing, Reynolds number, Lift coefficient, Drag coefficient
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