摘要
采用7组元6反应化学动力学模型,通过数值方法研究了真实气体效应对阿波罗(Apollo)返回舱流场及气动力特性的影响.并利用典型弹道点的飞行和实验数据验证了化学非平衡流计算程序的可靠性.计算结果表明:真实气体效应主要发生在物面附近很薄的激波层内,真实气体效应使得激波脱体距离减小;真实气体效应使阻力系数和升力系数增加,且在小攻角时增加幅度最大;真实气体效应产生附加的低头力矩,使压心位置后移.真实气体效应的影响随着马赫数的增加变化不明显.
Based on a seven-species and six-reaction chemical kinetical mode, the real gas effects on the flow field and the aerodynamic characteristics of the Apollo return command module in a chemical nonequilibrium flow at high temperature are investigated numerically. The code presented here for the chemical non-equilibrium flow is validated through the flight data and the experimental data. Results show that the real gas effects are prominent in some regions of quite thin shock wave layers close to the wall surface, and the outstanding distance of the shock wave is reduced, and the drag coefficient and the lift coefficient are increased with the largest amplitude at a small attack angle. The real gas effect results in some additional downward force moment, moving the pressure centre backward. The larger the freestream Math number, the greater the real gas effect on the aerodynamics of the return command module.
出处
《力学与实践》
北大核心
2013年第3期27-34,共8页
Mechanics in Engineering
关键词
返回舱
真实气体效应
气动特性
return command module, real gas effect, aerodynamic characteristics
