ACTA AERONAUTICAET ASTRONAUTICA SINICA >
Reverse jet flow control by plasma synthetic jet actuator in high speed flow field
Received date: 2022-07-09
Revised date: 2022-07-27
Accepted date: 2022-08-16
Online published: 2022-08-31
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.
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 . DOI: 10.7527/S1000-6893.2022.27789
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