Effect of angle of attack on the performance of the supersonic intake for High Mach Integrated Control Experiment (HIMICO)
Effect of angle of attack on the performance of the supersonic intake for High Mach Integrated Control Experiment (HIMICO)
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DOI：
10.1016/j.ast.2022.107687
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发表时间：
2022-06
影响因子：
5.6
通讯作者：
Manami Fujii;Shogo Ogura;Tetsuya Sato;H. Taguchi;A. Hashimoto;Takashi Takahashi
中科院分区：
文献类型：
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作者：
Manami Fujii;Shogo Ogura;Tetsuya Sato;H. Taguchi;A. Hashimoto;Takashi Takahashi
在高马赫综合控制实验（HIMICO）中，为掌握迎角对超音速进气道性能的影响，进行了实验、数值和理论研究。简单激波（TFD）理论分析结果表明，正攻角增大了质量捕获比（MCR）和总压恢复（TPR）。事实上，将2.5°AoA与- 2.5°AoA的CFD计算结果进行比较，当喷嘴喉道高度（HNT）为12.5 mm时，MCR和TPR分别增大了21pt和5pt。造成这些现象的主要因素是进气道投影面积的增大和斜冲系统的改变。另一方面，TFD错误地估计临界状态下的HNT和TPR，因为在TFD中产生的是伪激波，而不是末端正常激波。为此，利用CFD技术研究了伪激波的特性。结果发现，伪激波造成的总压损失大于正常激波造成的总压损失，并且由于进气喉部马赫数的降低，当AoA为正时，总压损失变小。利用CFD计算结果，根据进气喉部马赫数与伪激波总压损失的关系方程，建立了估算临界状态下TPR和HNT的模型。
Experimental, numerical and theoretical investigations are carried out to grasp the effect of angle of attack (AoA) on the performance of the supersonic intake for High-Mach Integrated Control Experiment, HIMICO. The results of theoretical analysis using simple shock wave (TFD) suggests that mass capture ratio (MCR) and total pressure recovery (TPR) are increased with positive angle of attack. In fact, comparing the result of 2.5 deg AoA with that of −2.5 deg AoA gained by CFD, MCR and TPR become 21pt and 5pt larger when the nozzle throat height (HNT) is 12.5 mm. The main factors of these phenomena are the increased projected area of the intake entrance and the change of the oblique shock system. On the other hand, TFD incorrectly estimates HNT and TPR in critical state because the pseudo-shock wave is generated instead of the terminal normal shock wave considered in TFD. So the characteristics of the pseudo-shock wave are investigated by CFD. As a result, it was found that the total pressure loss due to the pseudo-shock wave is larger than that of the normal shock wave, and that the total pressure loss becomes smaller with positive AoA due to the decrease in the Mach number at the intake throat. Using the CFD results, we created a model to estimate TPR and HNT in the critical state from the relational equation between the intake throat Mach number and the total pressure loss due to the pseudo-shock wave.