高超声速双楔激波干扰定常射流控制试验研究

doi:10.7527/S1000-6893.2023.28813

Abstract

Abstract:

Shock interaction is a widespread phenomenon in supersonic/hypersonic vehicles， bringing serious problems such as pressure load and thermal load increase. To reduce the thermal load in the shock interaction zone， we conduct an experimental study on the control of Type-V and Type-Ⅳ double wedge shock interaction using air source/self-sustaining steady jet in hypersonic flow. The control and heat reduction mechanism of double wedge shock interaction by air source steady jet is embodied in two aspects： isolation effect of jet flow and structural change effect of shock interaction. Under the jet control， the interaction intensity between the shock interaction zone and the wall is weakened， and the structure of the flow field changes significantly， which is no longer the typical Type-V and Type-Ⅳ shock interaction， and the heat flux on the wall also decreases correspondingly. Larger jet pressure ratios lead to stronger isolation effect and structural change effect， as well as larger reduction ratios of heat flux extremum. The maximum reduction ratio of heat flux extremum of Type-V and Type-Ⅳ shock interaction is about 81.2% and 79.6%， respectively. Self-sustaining steady jet is generated by collecting high speed flow energy. Under the control of self-sustaining jet， the heat flux extremum of the double-wedge Type-V and Type-Ⅳ shock interaction zones decreases by about 20% and 4.5% respectively. Improving the pressure ratio of the self-sustaining jet is the key to improving the control and heat reduction effect of shock wave interaction.

Key words: shock interaction, double wedge, steady jet, active flow control, heat reduction

CLC Number:

Wei XIE, Zhenbing LUO, Yan ZHOU, Qiang LIU, Jianjun WU, Hao DONG. Double wedge shock interaction control using steady jet in hypersonic flow: Experimental study[J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(7): 128813-128813.

Figures/Tables 13

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工况	试验模型	二楔角度/（°）	射流压比
1-1	30-60基准	60	0
1-2	30-60气源	60	1.2
1-3	30-60气源	60	3.0
1-4	30-60气源	60	4.8
1-5	30-60气源	60	6.6
1-6	30-60气源	60	8.4
1-7	30-60气源	60	10.2
1-8	30-60气源	60	12.0
1-9	30-60自持	60	1.7
2-1	30-75基准	75	0
2-2	30-75气源	75	1.2
2-3	30-75气源	75	3.0
2-4	30-75气源	75	4.8
2-5	30-75气源	75	6.6
2-6	30-75气源	75	8.4
2-7	30-75气源	75	10.2
2-8	30-75气源	75	12.0
2-9	30-75气源	75	13.8
2-10	30-75气源	75	15.6
2-11	30-75气源	75	17.4
2-12	30-75自持	75	1.7

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Double wedge shock interaction control using steady jet in hypersonic flow: Experimental study

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