Some influence factors in aerodynamic heat transfer numerical simulation of jet-interaction flow

When simulate the aerothermal environment of thrust jet and its interaction flow on an engineering vehicle geometry, people always use some approximate modeling to the full chemical reaction flow, then the influence to the simulation results of an approximate treatment for real gas and the modification to internal geometry of the thruster nozzle must to be manifested. By doing numerical test and compare results of some calculations, two main influence factors were studied to show the laws in approximate numerical simulation. One of which is how the possible modifications to thruster internal geometry influence on wall heat flux distribution of jet-interaction flow field. The second is when using a methodology of ideal gas equivalence to model fuel thruster jet, how different matching methods of the thruster exit boundary thermodynamic parameters influence the exhaust jet morphology and wall heat flux distribution. These computation results reveal the two main influence factors in aerodynamic heat transfer approximate simulation of thrust jet, and could be used to guide engineering applications.