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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

Technical Report: Aerodynamic Characteristics of the NACA 0015 Airfoil 1. Abstract Download 0015 txt

Data is typically collected in a low-speed wind tunnel using an inclined tube manometer to measure pressure distributions and force balances to record lift and drag. 3.3 Numerical Simulation (CFD) The NACA 0015 profile is defined by its 15% thickness

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