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为了准确预估转捩起始点位置,采用考虑转捩的γ-Reθ湍流模型,对锥体高超声速流场和平板激波/边界层干扰流场进行了验证,有效地预测了边界层转捩位置、激波/边界层干扰的复杂波系结构、分离流动以及气动加热现象,且比传统的湍流模型具有更高的可信度.设计了三压缩角和等熵压缩型面进气道流场,计算结果表明,等熵压缩型面设计具有较好的喉部通流能力和较高的总压恢复性能,在进气道喉部之后,两方案性能基本一致.
In order to accurately estimate the starting position of the transition, the γ-Reθ turbulence model considering the transition was used to verify the hypersonic flow field and the plate shock / boundary layer disturbance flow field, which effectively predicted the position of the boundary layer transition , Complex wave structure of shock / boundary layer disturbance, separation flow and aerodynamic heating, and have higher reliability than the traditional turbulence model.Three compression angle and isentropic compression profile inlet flow field The results show that the design of isentropic compression profile has good throat flow capacity and high total pressure recovery performance. After the inlet throat, the performance of the two schemes are basically the same.