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The comparison between experimental and numerical data for the NACA 0015 shows high correlation, though CFD models often slightly under-predict drag at high angles of attack. This profile remains a robust choice for applications requiring predictable symmetric performance.

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The NACA 0015 exhibits a "trailing edge stall," where the flow separation begins at the rear and moves forward as the AoA increases. 5. Conclusion

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 This profile remains a robust choice for applications

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

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) Conclusion The NACA 0015 profile is defined by

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