Unsteady Behavior of Long-Penetration Mode with a Counterflowing Jet
Publication: Journal of Aerospace Engineering
Volume 36, Issue 1
Abstract
Large drag force and severe heating are two major issues encountered in the development of hypersonic vehicles. As an active control technology, the application of a counterflowing jet to hypersonic vehicles to reduce the wave drag and heat flux has attracted extensive attention. However, the flow instability associated with the counterflowing jet, particularly the instability related to the large oscillation of bow shock in front of the vehicle at a long penetrating mode, remains to be further studied. In this study, a numerical investigation for a hemispherical nose with a counterflowing jet in a hypersonic flow is carried out by solving the Navier-Stokes equations, based on a solver developed on the OpenFOAM platform. The instability characteristics of bow shock, the drag reduction mechanism, and the flow structure around the nose specially for a long penetrating mode are studied in detail. The results show that with a counterflowing jet, the shock standoff distance can be increased largely and the drag force reduced significantly, and under a specific jet pressure ratio the averaged shock standoff distance and drag coefficient can reach to the values of 3.5 and 0.45 times those without a jet, respectively. The drag force varies periodically as the shock wave moves back and forth in front of the hemisphere and the oscillation frequencies of the force and the shock standoff distance are the same, but there is a phase difference between them. It is found that the bow shock oscillation at a long penetrating mode is usually asymmetrical in time, and the oscillation also occurs at a short penetrating mode when the jet pressure ratio is in a certain range, but it is symmetrical in time and the amplitude of the oscillation is usually smaller. The results of present study may provide useful information for the practical application of counterflowing jets.
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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
The authors acknowledge support from the Basic Research Project of Shenzhen Science and Technology plan (No. JCYJ20170307151117299) and the Basic Research Program of Science and Technology Project of Shenzhen (No. JCYJ20180306171753070).
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Published In
Journal of Aerospace Engineering
Volume 36 • Issue 1 • January 2023
Copyright
© 2022 American Society of Civil Engineers.
History
Received: Jan 27, 2022
Accepted: Jul 5, 2022
Published online: Oct 17, 2022
Published in print: Jan 1, 2023
Discussion open until: Mar 17, 2023
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