Exhaust plume simulation of solid rocket

The problem of numerical prediction of rocket plumes exhausting into supersonic airflow is discussed. The Diago-nalized Upwind Navier-Stokes (DUNS) code is applied to simulate the exhaust plume of two different solid rockets. The code originated as a single-block, perfect gas 3-D Navier-Stokes solver, with a two-equation (q-ω) turbulence model, and the code uses a diagonalized ADI algorithm to integrate the governing equations. First, a solid rocket nozzle is calculated, all the conditions of the nozzle come from the reference paper, and the results are consistent with that of the reference paper too. And then, another rocket nozzle is calculated. We calculated it at five different conditions, three different heights and thee different flight Mach numbers. We achieved all the results that we wished. Some other researches about the exhaust plume can be developed successfully based on these results.