Numerical investigation of gurney flap aerodynamics over a NACA 2412 airfoil

• DOI: 10.1063/1.5044330
• Publication Date: 2018-07-14T00:30:39Z
• Authors: Sanjoy Kumar Saha; Md. Mahbubul Alam; A. B. M. Toufique...
• Keywords: Stall (fluid mechanics); Trailing edge; NACA airfoil; Leading edge

From the time of its invention, Gurney flap has been successfully employed as high lift augmentation device to enhance aerodynamic performance modern aircraft wings. These small flaps are located perpendicularly at suction side an airfoil near trailing edge. By addition gurney wake is stabilized which ensures laminar flow over and thus shifts shock. This study investigated effect a on NACA 2412 for subsonic condition. Flap height ranges from 2% 5% chord length. The investigation was evaluated 0° 32° angle attack under Mach number. numerical analysis performed using Computational Fluid Dynamics program predict field. shows that optimal size always below boundary-layer thickness edge it tends increase drag ratio significantly. with 2%C provides best rather than 3, 4 flap. concludes suggestion may lead reduction in regions, thus, increasing lift-to-drag before stall.