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首页> 外文会议>4th European Symposium on Aerothermodynamics for Space Vehicles, Oct 15-18, 2001, Capua, Italy >REAL GAS EFFECTS ON BLUNT CONE/FLARE CONFIGURATIONS
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REAL GAS EFFECTS ON BLUNT CONE/FLARE CONFIGURATIONS

机译：钝锥/火炬配置的真实气体效应

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摘要

Blunt cone/flare experiments performed at CUBRC under hypersonic laminar flow conditions have been numerically rebuilt, the goal being to assess real gas effects on the aero-thermal loads occurring over the cone/flare configuration. All the fluid dynamic structures characterizing these flow fields, that well represent re-entry vehicle aerothermodynamics, have been qualitatively predicted although some doubts still exist about the flow modelling of high Reynolds number low enthalpy cases. Present computations are still grid-dependent in the cone/flare junction area and in terms of flare peak heating, hence definitive conclusions about the aero-thermal loads cannot be drawn. The external flow structures are steady, while some unsteadiness arises inside the recircula-tion region thus making numerical solutions sometimes unstable. The aero-thermal loads in regions of shock/shock and shock wave/boundary layer interaction are enhanced by real gas effects, while the separated area is strongly reduced in high enthalpy air conditions.
机译：在数值上重建了在高超声速层流条件下在CUBRC进行的钝锥/扩口实验，目的是评估实际气体对锥/扩口构型上发生的空气热负荷的影响。定性地预测了表征这些流场的所有流体动力学结构，这些结构很好地代表了再入飞行器的空气热力学，尽管对于高雷诺数低焓情况下的流动模型仍然存在一些疑问。目前的计算仍然取决于锥/火炬交界处以及火炬峰值加热的网格，因此无法得出关于空气热负荷的明确结论。外部流动结构是稳定的，而在再循环区域内部会出现一些不稳定的情况，因此有时数值解会变得不稳定。真实的气体效应增强了冲击/冲击和冲击波/边界层相互作用区域中的空气热负荷，而在高焓空气条件下，分离区域却大大减小了。

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