This paper examines thermal response behind the high-Mach integrated control (HIMICO) experiment’s engine. In this experimental aircraft, instruments must be protected from heat load due to exhaust gas; therefore, a coupling calculation between the fluid and the wall is conducted to confirm the performance of HIMICO’s thermal protection system (TPS). First, the validity of the coupling calculation is confirmed through comparison with aerodynamic heating on a hollow cylinder. The present calculation result can reproduce the surface temperature distribution on the cylinder better than previous work has managed because we consider the turbulence effect. Second, one-dimensional heat-transfer analysis is conducted on the external nozzle, and the appropriateness of the calculation result is confirmed through comparison with the ramjet-engine experiment. Finally, a coupling calculation between the fluid and the wall is conducted to investigate the local temperature distribution. The calculation result indicates that the temperature increase easily meets design requirements and that TPS performance is sufficient.

本文研究了高马赫集成控制 (HIMICO) 实验发动机背后的热响应。在这架实验飞机中，必须保护仪器免受废气引起的热负荷；因此，进行流体和壁之间的耦合计算，以确认 HIMICO 的热保护系统 (TPS) 的性能。首先，通过与空心圆柱体上的气动加热进行比较，证实了耦合计算的有效性。由于我们考虑了湍流效应，当前的计算结果可以比以前的工作更好地再现圆柱体的表面温度分布。其次，对外喷管进行一维传热分析，通过与冲压发动机实验对比，验证了计算结果的合理性。最后，进行流体与壁面之间的耦合计算，以研究局部温度分布。计算结果表明，温升很容易满足设计要求，TPS性能足够。