Numerical Investigation of a Generic Rocket Base Flows under Subsonic Conditions

Abstract

The base flow of a generic rocket model is investigated numerically with different levels of turbulence modeling. The comparison with the experiments shows at the nominal flow conditions significant deviations in the horizontal plane and the base pressure distribution. A simulation of the open test section is presented, which indicates on the one hand a correction of the measured pressure values and on the other hand an angle ofattack modification in comparing the DES results with the experimental values. Based on both correction the DES results agree well with the experiment. A strong sensitivity towards small angles of attack has been observed in the experiments but not in respective RANS solutions. Although no variation of the angle of attack has been feasible with a DES, the DES seems to capture this sensitivity.