ACTA AERONAUTICAET ASTRONAUTICA SINICA >
Experimental Study of Hypersonic Inward Turning Inlets with Innovative Basic Flowfiled
Received date: 2013-01-21
Revised date: 2013-03-05
Online published: 2013-03-11
Supported by
National Natural Science Foundation of China (90916029)
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.
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 . DOI: 10.7527/S1000-6893.2013.0159
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