Abstract
We performed numerical simulations of supersonic conical nozzle flows and supersonic flow past wedge-shaped test pieces. We used the point-implicit MacCormac scheme to solve the governing equations. Chemical source terms were calculated using the Park model. The equation of Millikan was used to calculate relaxation time of vibrational energy of diatomic molecules. We consider two reservoir conditions : design and experimental. From these numerical simulations, the following conclusions are obtained. (1) Due to the effect of the boundary layer in the nozzle flow, the Mach number at the exit becomes smaller compared with the inviscid one-dimensional result. (2) The flow field can be considered as chemically frozen downstream from the shock wave. (3) The behavior of vibrational energy downstream from the shock wave in the experimental conditions on the ground is different from that in flight conditions at high altitude.
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