高超飞行器热化学非平衡及稀薄滑移流动模拟

Simulaton of therochemical nonequilibrium and rarefied-slip flows for hypersonic flight vehicles

稀薄滑移效应对高超飞行器气动特性产生重要影响。基于HyFLOW软件构建适用于热化学非平衡流动模拟的速度滑移和温度滑移边界条件,同时分别选取猎户座(Orion)飞船返回舱、OREX试验飞行器及类“哥伦比亚号”(OV102)航天飞机等典型高超飞行器,开展稀薄滑移流动模拟及其相关气动特性预测分析。研究表明:HyFLOW软件的稀薄滑移边界模型计算可靠,在预测热化学非平衡及稀薄滑移耦合效应相关的气动力、气动热特性方面具有较高的计算精度,能够满足工程复杂外形的仿真应用需求;稀薄滑移效应可显著降低热流峰值和减小热流峰值分布区域大小,相比于无滑移条件,其在类OV102航天飞机外形中预测的头部热流峰值最大降低了约45%,机翼前缘热流峰值最大降低了约20%。

The rarefied slip effect has a significant impact on the aerodynamic characteristics of hypersonic vehicle.Based on HyFLOW software,velocity slip and temperature slip boundary conditions suitable for thermochemical nonequilibrium flows are constructed.Meanwhile,the rarefied slip flows over the usual hypersonic vehicles of the Orion reentry capsule,OREX experiment flight vehicle,and the Columbia OV102-like space shuttle are simulated,and the associated aerodynamic properties are also anticipated and studied.Research results indicate that the rarefied slip boundary model in HyFLOW software is reliable,and has high computational accuracy in predicting the aerodynamic and aerothermal characteristics related to coupling effects of thermochemical nonequilibrium and rarefied slip.It can meet the simulation application requirements of complex engineering configurations.In addition,the rarefied slip effect can significantly reduce the peak value of heat flux and its distribution area.The peak heat flow of the OV102-like space shuttle's nose is anticipated by the slip condition to be,at most,45%less than that of the no-slip condition,and,at most,20%less than that of the leading edge of the wing.