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): Remains low at low AoA but increases exponentially as the airfoil approaches stall due to flow separation.

This paper investigates the performance of the NACA 0015 airfoil, a symmetric 4-digit series profile with a 15% thickness-to-chord ratio. Using data derived from both experimental wind tunnel tests and CFD simulations, we analyze the lift and drag coefficients ( CLcap C sub cap L CDcap C sub cap D

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The NACA 0015 profile is defined by its 15% thickness. As a symmetric airfoil, it produces zero lift at a 0∘0 raised to the composed with power angle of attack. 15% of the chord length. Camber: 0% (Symmetric). 3.2 Experimental Setup

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Simulations are conducted using software like ANSYS Fluent or OpenFOAM . The mesh is refined near the leading and trailing edges to capture boundary layer separation accurately. 4. Results and Discussion Lift Coefficient ( CLcap C sub cap L