Numerical Study on Interaction Between Gas Jet and Supersonic Flow in Solid Rocket Motor
In order to obtain the interaction characteristics of supersonic flow and solid rocket motor ( SRM ) range stage gas jet,based on computational fluid dynamics ( CFD),a high-precision numerical calculation scheme is used to simulate the in-teraction flow field of SRM gas jet and supersonic flow under different working conditions. The whole flow field can be roughly divided into the outer field,the recirculation zone and the plume zone. Under a certain nozzle drop pressure ratio,with the in-crease of altitude,the nozzle flow separation phenomenon gradually disappears,the jet wave nodes decrease,and the distance between the formation of the first incident shock wave and the nozzle outlet increases. On the other hand,the increase of alti-tude will cause the increase of the recirculation zone wall temperature rise. In addition,the actual working pressure is more than 30％ lower than the static pressure due to the rapid expansion of supersonic inflow at the rear edge of the projectile.
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