Base heat flux measurement techniques in impulse hypersonic test facilities
Base heat flux measurement techniques in impulse hypersonic test facilities
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DOI：
10.1002/htj.21501
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发表时间：
2019-07
影响因子：
4.9
通讯作者：
Kiran J. Irimpan;V. Menezes;K. Srinivasan
中科院分区：
文献类型：
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作者：
Kiran J. Irimpan;V. Menezes;K. Srinivasan
安全高效的高超音速飞行任务需要进行详尽的测试，以捕获用于优化热防护系统的表面热流。虽然低，基本传热率仍然是相关的，他们的估计是至关重要的。冲击式高超音速试验设施，如激波风洞，通常用于这种估算试验。本文比较了当代热流测量技术，即E型同轴热电偶，铂薄膜，和原子层热电堆在一个高超音速激波风洞的底部按比例缩小的返回舱。使用压力测量确保基流建立。测量结果表明，底部驻点热通量约为前体驻点热通量的2%~ 3%，并且稳定在43.2 ± 2.4的近似无量纲建立时间。
Safe and efficient hypersonic missions require exhaustive testing to capture the surface heat flux used in optimizing thermal protection systems. Though low, base heat transfer rates are still relevant and their estimation is of the utmost importance. Impulse hypersonic test facilities like the shock tunnel are commonly used for such estimation tests. The present paper compares contemporary heat flux measurement techniques, namely, E‐type coaxial thermocouples, Pt‐thin films, and atomic layer thermopiles in a hypersonic shock tunnel at the base of a scaled‐down re‐entry capsule. Base flow establishment is ensured using pressure measurements. The measurements indicated that the base‐stagnation point heat flux was approximately 2% to 3% of the forebody stagnation heat flux and it stabilized at an approximate nondimensional establishment time of 43.2 ± 2.4.