采用新型基准流场的高超内收缩进气道试验研究

doi:10.7527/S1000-6893.2013.0159

Abstract

Abstract:

The innovative basic flowfield with curved centre body has high pressure efficiency and weak reflected shock, so a hypersonic inward turning inlet with rectangular to circular shape transition is designed with this kind of basic flowfield and tested at design point Mach 6.0 in a hypersonic wind tunnel. The pressure distributions on top wall and cowl wall and the parameters distribution at isolator exit is obtained in this experiment. The results of experiment and numerical simulation turn out the pressure gradient increasing at initial part, then deceasing, and the pressure distribution in internal part has characteristics of two-pressure-rise, and the pressure rise is low, so the flowfield of internal part is good. Because the shock in the internal part of inlet is weak, the inlet has high pressure recovery coefficient, about 0.518, and generates a compression ratio of 52. The critical back pressure ratio of this inlet is above 144. The innovative basic flowfield can improve the flowfield of internal part and isolator and increase the pressure recovery of the inlet with rectangular to circular shape transition.

Key words: inward turning inlet, hypersonic inlet, basic flowfield, numerical simulation, wind tunnel experiment

CLC Number:

V231

NAN Xiangjun, ZHANG Kunyuan, JIN Zhiguang. Experimental Study of Hypersonic Inward Turning Inlets with Innovative Basic Flowfiled[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2014, 35(1): 90-96.

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Experimental Study of Hypersonic Inward Turning Inlets with Innovative Basic Flowfiled

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