Application of Wray-Agarwal Turbulence Model to Axisymmetric Subsonic and Transonic Flows

This paper describes the problem setup, implementation, and numerical results obtained with the commercial CFD software ANSYS Fluent to test the accuracy of the one-equation Wray-Agarwal (WA) turbulence model in comparison to the commonly used one-equation Spalart-Allmaras (SA) turbulence model by computing two axisymmetric benchmark problems, namely the subsonic flow past an axisymmetric after-body and the transonic flow past Sandia axisymmetric bump. The axisymmetric after-body case features low speed flow in near separation conditions where it was found that the Wray-Agarwal model and the Spalart-Allmaras model produced nearly identical results. The Sandia transonic axisymmetric bump case features a complex flow in which shock induced separation occurs over the geometry. In this test case the Wray-Agarwal model was seen to improve accuracy over the Spalart-Allmaras model in terms of pressure distribution and separation prediction on the bump.