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Test of non-uniform nozzle plume for air-breathing hypersonic vehicle
Received date: 2016-03-08
Revised date: 2016-08-29
Online published: 2017-04-11
The pressure test for the inner-outer flow interaction area are conducted at the 0.5 m hypersonic wind tunnel in China Aerodynamics Research and Development Center. The test are conducted at the conditions of uniform and non-uniform incoming flow. Using non-uniform inner nozzle, the pressure on the afterbody expansion surface and the horizontal wing surface of the aircraft can be measured by simulating the non-uniform incoming flow of the aircraft nozzle. High speed schlieren is used to observe the flow field structure of the interaction areas of the plume, and the rules of influence of non-uniform incoming flow on pressure distribution on the afterbody expansion surface and horizontal surface of the aircraft nozzle can be got under different conditions. The test results show that the non-uniform incoming flow of the nozzle has significant influence on wall surface pressure distribution and flow field structure of the aircraft. The non-uniform characteristic of the nozzle's incoming flow cannot be ignored in simulation of air breathing hypersonic vehicle plume. It can be seen from the test result that the pressure of the non-uniform plume's core area is obviously higher than that of the uniform plume; while outside the core area, the non-uniform plume has a slightly smaller action area than the uniform plume, and the interaction area and intensity of non-uniform plume and outflow is also smaller than those of uniform plume. The uniform plume has distinct expansion waves in the exit area of the nozzle, and the expansion angles of interaction shock wave and shear layer of the uniform plume are larger than those of the non-uniform plume.
HE Xuzhao , QIN Si , WEI Feng , LE Jialing . Test of non-uniform nozzle plume for air-breathing hypersonic vehicle[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2017 , 38(3) : 120199 -120199 . DOI: 10.7527/S1000-6893.2016.0246
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