Improvement of NACA6309 Airfoil with Passive Air-Flow Control by using Trailing Edge Flap
This study uses CFD simulations to analyze 16 configurations of the NACA6309 airfoil with trailing-edge flaps, finding that a 1° up-flap offers the best aerodynamic performance while the 10° down-flap performs the worst.
Sep 24, 24240
Effects of Trailing Edge Thickness on NACA 4412 Airfoil Performance at Low Reynolds Numbers: A CFD Analysis
This study modifies the NACA 4412 airfoil's trailing edge thickness using CFD, finding that a 0.8% thickness offers optimal performance with improved lift and lift-to-drag ratio, while a 0.2% thickness reduces overall performance.
Sep 24, 24240