基于混合网格上的高温非平衡流的数值模拟

新一代再入飞行器及空间传输系统需要了解其飞行时的气动问题及热力学问题。数值模拟高空、低密度、高熵及非平衡流动是一具有挑战性的问题。本文针对带座舱飞船高超声速再入大气过程中存在的严重气动加热现象,利用混合网格及Osher逆风格式,数值求解了三维化学非平衡Navier-Stokes方程,其中化学模型是5组分1 7个化学反应的空气化学模型,对带座舱飞船再入高度为40 km和马赫数为2 0 ,1 0的化学非平衡流场进行了数值模拟,给出了迎角为0°和2 0°情况下的各个组分的密度分布、压力等参数,并与量完全气体的计算结果进行了比较。

Simulation of Hypersonic Non-Equilibrium Flow Using Hybrid Grids

The design of a new generation of re-entry space vehicles and space transportation systems requires to study aerodynamics and thermodynamics problems to the flight trajectory. Numerical simulation of low-density, high-enthalpy and strongly non-equilibrium gas flows near space vehicles at high-altitudes is now rather problematic. In this paper, the real-gas effect is used for the simulation of supersonic flow past the space shuttles. The hybrid grid and Osher schemes are involved to solve the non-equilibrium Navier-Stokes equations. The chemical reaction model includes 17 equations for 5 species. The hypersonic flow past the space-shuttle in the 40 km altitude and with 20, 10 Mach number is simulated. The pressure distribution and density distribution for each specie are demonstrated and compared with the perfect gas results.