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Simulations of the aerodynamics performance of NACA 4312 airfoil at various gurney flap angles and incoming airspeed (wind velocities) have been conducted. The gurney flap's size was set at 5.0% length of the chord line. Two airfoil models with gurney flap at 45° and 90° were simulated and compared with the results of plain airfoil (without gurney flap) model with the incoming airspeed of 10.0 m/s, 70.0 m/s and 200.0 m/s. The results have shown that increasing the value of gurney flap angle to 45° and 90° will increase the lifting force of the airfoil and decrease the drag force.

Simulating the Aerodynamics Profiles of NACA 4312 Airfoil in Various Incoming Airspeed and Gurney Flap Angle