等离子体合成射流激励器高速流场逆向喷流控制

doi:10.7527/S1000-6893.2022.27789

Abstract

Abstract:

As a special aerodynamic phenomenon accompanying high-speed flight， shock wave has an important impact on the safety and performance of aircraft. Effective flow control has great significance in improving the aerodynamic/thermal environment of aircraft. Plasma has attracted more and more attention in recent years because of its simple structure， small mass， fast frequency response， large excitation bandwidth， adjustable excitation intensity， easy arrangement and no auxiliary control system. In this paper， high speed schlieren and laser dynamic pressure sensor are used to study the unsteady control of bow shock by counter jet of plasma synthetic jet. The results show that plasma synthetic jet has a strong flow control effect， whose control time is more than 600 μs. With the decrease of jet pressure， the controlled bow shock presents short penetration mode and long penetration mode changes. The debugging process of the two modes has a certain degree of drag reduction effect on the model.

Key words: plasma synthetic jet, flow control, bow shock wave, long penetration mode, short penetration mode

CLC Number:

V211

Zheng LI, Cong XU, Jian ZHANG, Mengmeng LI, Yilei MA, Guanghui BAI. Reverse jet flow control by plasma synthetic jet actuator in high speed flow field[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(S2): 225-232.

Figures/Tables 14

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References 24

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Reverse jet flow control by plasma synthetic jet actuator in high speed flow field

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