Computational Study of Transonic Flow over a RAE- 2822 Airfoil by Using FLUENT Code

The main purpose of the present study is to investigate the characteristics of transonic flow under variation of viscosity type (Inviscid, Realizable K.E., Reynolds Stress Model, Large Eddy Simulation (LES)) as the most interest is the location and size of the shock wave as well as the pressure coefficient on both sides of the airfoil surface with a commercial code for Computational Fluid Dynamics (CFD). Gambit Code was used to build the model and the flow equations solved by using Fluent Code after the boundary conditions applied to the model. The comparison was made with recent researches based on same airfoil type neE 2822, angleof attack (2.310) and Mach number (0.729). The results show good agreement with the references but with slightly viscosity effect on the pressure coefficient and shock wave location and size.