Effect of Flap on the Aerodynamic Characteristics of Supercritical Airfoil RAE 2822
Iman Jabbar Ooda
Department of aeronautical Engineering, University of Baghdad, Baghdad-Iraq
Corresponding Author Email: firstname.lastname@example.org
This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.
The influence of trailing edge flap on basic aerodynamic characteristics such as CP, CL, and CD is investigated using Ansys Fluent (14.5) software to analyze the flow over a supercritical RAE 2822 airfoil with a 25% c trailing edge flap.The airfoil will be modelled at 0°angle of attack with flap settings of 2°, 4°, 6°, 8°, and 10° at M=0.729 and α=2.79°. The transonic compressible flow was modeled using the k-ω (SST) turbulence model. According to the calculations, the lift and drag coefficients increase as the flap angle increases, and the shock travels downstream.According to this research, when the flap is deflected, The flow is trapped beneath the airfoil, causing a decrease in flow velocity and a build-up of pressure. Simultaneously, as the gradient of adverse pressure rises with flap deflection, so does the gradient of positive pressure.the flow separation on the flap surface increases. The theoretical conclusions were compared to previously publish computational work and found to be in good accord.