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本文着重研究起飞状态下二元超音速进气道进气口内气流流动的动态特性。实验结果表明,在唇口分离区再附着点下游的靠近唇口壁面和在几何喉道下游邻近的通道截面中部,各有一个强的气流总压脉动区,其最大紊流度达0.0825;而平均紊流度约为0.06。若对唇口内侧分离流采取有效的控制,紊流度峰值大大下降,平均紊流度由0.06降为0.032～0.031(在截面)。文中还就进气口内气流的总压信号与几何喉道附近气流的总压作了较为详细的相干分析。指出,在对唇口分离流采取有效措施之后,可以明显地改善其相干性。
This paper focuses on the dynamic characteristics of air flow in the inlet of a binary supersonic inlet under take-off condition. Experimental results show that there is a strong turbulent total pressure pulsation zone near the lip wall downstream of reattachment points in the lip / lip separation zone and mid-section of the channel adjacent to the downstream of the geometric throat, with a maximum turbulence of 0.0825. The average turbulence is about 0.06. If effective control was applied to the separation flow inside the lip, the peak turbulence sharply decreased and the average turbulence decreased from 0.06 to 0.032 to 0.031 (at the cross section). The article also made a more detailed coherent analysis of the total pressure of the airflow in the inlet and the total pressure of the airflow near the geometric throat. Pointed out that in the lip separation flow to take effective measures, it can significantly improve its coherence.