Open AccessNumerical Simulation of Flows Field Characteristics of High Altitude Liquid Rocket Exhaust Plume
Author(s) -
Qing Ye,
Zunyang Liu,
Jie Li,
Rongyuan Su
Publication year - 2020
Publication title -
iop conference series. materials science and engineering
Language(s) - English
Resource type - Journals
eISSN - 1757-899X
pISSN - 1757-8981
DOI - 10.1088/1757-899x/711/1/012110
Subject(s) - plume , rocket (weapon) , nozzle , rocket engine nozzle , mechanics , solid fuel rocket , physics , flow (mathematics) , aerospace engineering , field (mathematics) , direct simulation monte carlo , altitude (triangle) , shock wave , meteorology , environmental science , monte carlo method , propellant , thermodynamics , geometry , engineering , statistics , mathematics , dynamic monte carlo method , pure mathematics
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.