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): Remains low at low AoA but increases exponentially as the airfoil approaches stall due to flow separation. The NACA 0015 profile is defined by its 15% thickness

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

): Increases linearly with the angle of attack until reaching the stall point, typically between 12∘12 raised to the composed with power 15∘15 raised to the composed with power depending on the Reynolds number. Drag Coefficient ( CDcap C sub cap D

) across varying angles of attack (AoA) to identify stall behavior and efficiency. 2. Introduction