Author:
Ye Qing,Liu Zunyang,Li Jie,Su Rongyuan
Abstract
Abstract
The simulation of flow field structures of high altitude liquid rocket exhaust plume is of great significance for infrared radiation caclution. Considering the flow field’s symmetry construction, half of the 2-D zone was chosen as the calculation zone. In order to reduce the amount of calculation, we had made an equivalent reduction of the calculation zone. By using the direct simulation Monte Carlo (DSMC) method, a solver was constructed to simulate the flow field structure of the 120km altitude liquid rocket exhaust plume. The simulation results show that the flow field of the high altitude liquid rocket exhaust plume has the following three characteristics: a. the whole flow field indeed contains continuous flow and rarefied flow; b. rarefied gas effect plays a significant role to form a recirculation zones that surpass the nozzle; c. Non-equilibrium effect is remarkable in shock wave region and the boundary layers.
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