Flow field study of a supersonic jet exiting into a supersonic stream

The paper present a numerical / experimental investigation of the flow field resulting around a generic vehicle controlled by means of a lateral jet in supersonic motion. The experimental data are acquired in the DLR wind tunnel TMK in Cologne. To obtain the numerical results, the 3-D viscous, turbulent, Reynolds averaged hybrid Navier-Stokes Code Tau of DLR is used. Calculations are made for free stream Mach number of M* = 2.8 and various angles of attack. Several grids of varied density and structure and different turbulence models are investigated. The CFD results in terms of surface pressure, normal force coefficients, and jet interaction are in good agreement with the results from wind tunnel tests. On hand the numerical results it is shown important festures of the interaction mechanism between the lateral jet and the flow field originated by the motion of the vehicle