Abstract—A two-dimensional numerical investigation was performed to determine the effect of a Gurney flap on a NACA 23018 airfoil. An incompressible Navier-Stokes solver with Spalart-Allmaras turbulence model is used to predict the flow field around the airfoil. Gurney flap sizes of 0.5%, 1.0%, 1.5%, 2.0%, and 3.0% of the airfoil chord were studied.Computed results have been compared with available experimental data. Addition of Gurney flap increases the lift coefficient significantly with very little drag penalty if proper Gurney flap height is selected. Results showed that Gurney flaps produced a negative shift in the zero-lift angle of attack. The numerical solutions show the details of the flow structure at the trailing edge and provide a possible explanation for the increased aerodynamic performance.

Index Terms—Gurney flap, Lift enhancement, NACA23018 airfoil, Computational fluid dynamics

Cite: Masoud Jahanmorad Nouri, Habibollah Sayehvand, and Abolghasem Mekanik, "Numerical Investigation of Aerodynamic Characteristics of NACA 23018 Airfoil with a Gurney Flap," International Journal of Mechanical Engineering and Robotics Research, Vol.1, No.3, pp. 341-349, October 2012.