NUMERICAL SIMULATION OF HIGH-SPEED SEPARATION FLOW IN THE AEROSPACE PROPULSION SYSTEMS

摘要

Results of numerical simulation of turbulent flow around a high-speed vehicle are presented in the paper. Performance of several two- and three-equation turbulence models based on RANS approach is studied. Special attention is given to the various versions of the threeequation lag turbulence model. The model contains a relaxation type equation for the nonequilibrium eddy viscosity. In the paper, the results of numerical simulation of three highspeed turbulent flows are considered. The first flow is a turbulent separated flow in supersonic rocket nozzle. The second one is a high-speed flow near compression ramp. In addition, a hypersonic flow near scramjet inlet is calculated. It is shown that the lag turbulence model provides acceptable accuracy in most high-speed flows considered.