【摘要】 吸气式高超声速飞行器速域的不断拓展，使进气道部件在强烈的气动载荷以及热载荷作用下与外部流场耦合效应明显，同时高温流动中的真实气体效应会进一步加剧进气道内多场耦合关系的复杂性。通过在多场耦合仿真中考虑真实气体效应影响，针对壁面共轭耦合传热下高超声速进气道气动性能以及结构温度场的非定常变化进行数值模拟。研究发现：受壁温升高的影响，300 s时刻进气道出口气流温度相比初始时刻上升13.30%,压力升高13.53%,总压恢复系数下降2%,而流量系数几乎不发生变化。50 s时刻，唇缘和前缘处壁温达到2 350 K,内通道最高壁温为1 200 K,而在300 s时刻内通道最高壁温也接近1 900 K。因此在兼顾内通道防热设计的同时，要着重考量前缘及唇缘热防护设计的可靠性。更多还原

【Abstract】 With the increase of the flight speed of the air-breathing hypersonic vehicle, the coupling effect between the inlet and the external flow field is obvious under the strong aerodynamic load and thermal load. Meanwhile, the real gas effect in high temperature flow will further aggravate the complexity of the multi-physicalfield coupling relationship in the inlet. Based on the multi-physical field coupling simulation method considering the real gas effect, carries out the numerical simulation of the unsteady changes of the aerodynamic performance and structural temperature field of the hypersonic inlet under the wall conjugate coupled heat transfer. It is found that under the influence of the increase of wall temperature, the inlet outlet temperature at 300 s increases by 13.30% compared with the initial time, the pressure increases by 13.53%, and the total pressure recovery coefficient decreases by 2%, while the flow coefficient hardly changes. At 50 s, the wall temperature at the cowl-lip and leading-edge reaches 2 350 K, the maximum wall temperature of the inner channel is 1 200 K, and the highest wall temperature of internal contraction tunnel is close to 1 900 K at 300 s. Therefore, while taking into account the thermal protection design of internal contraction tunnel, the reliability of the design of the leading edge and lip should be taken into special consideration.更多还原