Comparative Study on Several Type of Turbulence Model Available In ANSY-Fluent Software for ONERA M6 Wing Aerodynamic Analysis
Abstract: A modern military aircraft (MMA) has been designed for extreme maneuverability particularly at a high angle of attack during subsonic, transonic or supersonic flight. Most of the wing design for a MMA is either highly swept wing or delta wing. The main purposes of MMA wing design is to avoid shock wave boundary formed at the nose of the fuselage as the speed of the aircraft approaches and exceeds transonic to supersonic speed. It also improves the stability of the aircraft when maneuver. Therefore, such aerodynamics features need to be investigate with used of computational fluid dynamic (CFD) method which it is used to analyze the flow characteristic past through a body. The most popular of commercial CFD software is ANSYS-Fluent software. The advantages of this software beside offer various flow solvers, this software also provides a various type of Turbulence Models can be implemented. In the present works had used five type Turbulence Models for evaluating the aerodynamic characteristics of the ONERA M6 wing model. These five turbulent models are: (1) Spalart-Allmaras, (2) k-ε Standard, (3) k-ε Realizable, (4) k-ω Standard and (5) k-ω SST turbulence models. The flow analysis are carried at two different angle of attacks namely at α = 3.060 and α = 6.060. These two angle of attacks correspond with Mach number = 0.84 and the Reynolds number Re = 11.76×. The comparison between ANSYS software with the experimental result as provided by AGARD AR-138 in term pressure coefficient distribution at several wing span location and overall aerodynamics characteristics in term lift coefficients shows that among those five turbulence models had been found that Spalart-Allmaras and k-ω SST turbulence model gives result close to the experimental results and the smallest number of iteration for getting a converge solution.