高超声速流场等离子体合成射流逆向喷流特性

doi:10.7527/S1000-6893.2022.27747

Abstract

Abstract:

To study the flow field characteristics of the reverse plasma synthetic jet under hypersonic conditions， experimental and numerical studies were carried out. In the hypersonic incoming flow with Mach number 8， the flow field variation of the reverse plasma synthetic jet was analyzed by comparing the schlieren and exciter outlet pressure monitoring results in the experiment and simulation. It is verified that under hypersonic conditions， the outlet pressure oscillation of the reverse plasma synthesis jet actuator is caused by multiple jets generated by multiple backfilling in the cavity， causing multiple shocks to sweep over the actuator outlet. The plasma synthesis jet increases the mass flow of the gas outside the jet area， while the precursor shock propagating upstream merges with the bow shock wave into a single shock. The vortex rings produced under the action of high-momentum jets， the low-pressure regions created by counter-currents， and the high-temperature low-density plasma jets reduce the local Mach number， resulting in an increase in the shock penetration depth.

Key words: plasma synthetic jet, flow control, hypersonic incoming flow, reverse jet, penetration depth

CLC Number:

V211.3

Zhengxue MA, Zhenbing LUO, Aihong ZHAO, Yan ZHOU, Wei XIE, Qiang LIU, Yinxin ZHU, Wenqiang PENG. Reverse jet characteristics of plasma synthetic jet in hypersonic flow field[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(S2): 192-203.

Figures/Tables 17

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参数	数值
喷管出口直径/m	0.5
风洞马赫数	5， 6， 7， 8
流量/（kg∙s^-1）	0.29~15.50
总压/MPa	0.04~1.0
总温/K	288~685
单位雷诺数/m^-1	6.47×10⁵~2.24×10⁷
模拟飞行高度/km	27~59
风洞运行时间/s	10
模型最大底部直径/mm	120
气源容积/m³	32
真空容积/m³	650

工况	总压 /atm	激励器腔体压力/Pa	总温 /℃	放电能量/J	电容 /μF
1	7.5	558.75	228	0.69	0.64
2	7.4	551.3	236	1.44	0.96
3	7.4	551.3	238	1.29	0.96
4	7.4	551.3	246	4.42	2.28

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Reverse jet characteristics of plasma synthetic jet in hypersonic flow field

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