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NACA 0012 Airfoil Pressure Analysis by cfw74595 is a document available to read on EtoBox.

This study investigates the aerodynamic performance of the NACA 0012 airfoil with Gurney flaps at various heights and angles of attack using computational fluid dynamics (CFD). Results indicate that the optimal Gurney flap height for maximum pressure difference and lift enhancement is approximately 4% of the chord length. The findings contribute to the design of efficient wing sections for aircraft by demonstrating the significant impact of flap height and angle on pressure distribution and lift generation.

Author

cfw74595

Language

EN