Experimental Study on the Dynamic Characteristics and Surface Arc Plasma Control of Shock Train in the Supersonic Inlet
Publication: Journal of Aerospace Engineering
Volume 35, Issue 5
Abstract
The oscillation characteristics and morphological changes of the shock train in the inlet expansion section and the control of the shock train by surface arc plasma were studied in Mach 2 supersonic flow. A wedge installed at the exit of the supersonic inlet created a throttling ratio of 50% to generate a shock train in the expansion section. A high-speed schlieren system was employed to capture the flow structure of shock train. The fast Fourier transform (FFT) and snapshot proper orthogonal decomposition (SPOD) methods were employed to identify the oscillations’ spectral characteristics and for modal analysis of the shock train, respectively. The results show that the oscillation of leading shock has the characteristics of multipeak frequencies with a range of , and the Mach disk dominates the low-frequency oscillation characteristics of the leading shock. The surface arc plasma actuation has a significant control effect on the shock train, realizing the conversion of the leading shock to the oblique shock.
Practical Applications
As the first exploration of controlling the shock train in a supersonic inlet by surface arc plasma actuation, we found that the leading shock is transformed from shock to oblique shock because of the excitation. During the whole control process, although the actuation changes the shape of the leading shock, the position of the leading shock hardly changes. The blast wave and the control gas bubble induced by the surface arc plasma actuation possibly can weaken the oscillation of the shock train and make it relatively stable in a certain position. In practice, there is a risk that the shock train will be pushed out of the inlet due to the back pressure. Surface arc plasma actuation may be able to balance the back pressure and suppress the excessive advance of the shock train. In the future, we will verify this and further expand the control ability of surface arc plasma actuation on the shock train.
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Data Availability Statement
Some or all data, models, or code that support the findings of this study are available from the corresponding author upon reasonable request.
Acknowledgments
This work is supported by the National Natural Science Foundation of China under Grant No. 51907205.
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Published In
Journal of Aerospace Engineering
Volume 35 • Issue 5 • September 2022
Copyright
© 2022 American Society of Civil Engineers.
History
Received: Oct 25, 2021
Accepted: May 6, 2022
Published online: Jul 8, 2022
Published in print: Sep 1, 2022
Discussion open until: Dec 8, 2022
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