摘要
本文针对带座舱飞船高超声速再入大气层过程中存在的严重气动加热现象 ,利用简单隐式TVD差分格式和激波捕捉法 ,数值求解三维化学非平衡Navier Stokes方程 ,其中化学模型是 7组分 1 5个化学反应的空气化学模型 ,对带座舱飞船再入高度为 70km和速度为6 7km/s的化学非平衡流场进行了数值模拟 ,给出了带座舱飞船再入迎角为 0°,1 0°和 2 0°情况下的壁面热流。
It is aimed at the aerodynamic heating phenomena of a capsule type hypersonic reentry vehicle in present paper, the flow fields over a capsule type hypersonic reentry vehicle is simulated numerically using 3 D chemical non equilibrium Navier Stokes equations with the Air chemical model of 7 species 15 reactions. 3 D chemical non equilibrium Navier Stokes equations is solved by the simple implicit TVD differencing scheme and the approach of capturing the shock. The steady state simulations are performed at an altitude of 70 km and at free stream velocity of 6 7km/s , and the numerical results predict the distributions of the heat transfer rate, the surface pressure and the electron number density at angles of attack of 0°,10°and 20°.
出处
《空气动力学学报》
CSCD
北大核心
2002年第2期239-245,共7页
Acta Aerodynamica Sinica
