Novel Osculating Flowfield Methodology for Hypersonic Waverider Vehicles Based on Variable Shock Angle
Publication: Journal of Aerospace Engineering
Volume 31, Issue 4
Abstract
This study proposes a variable shock angle osculating flowfield waverider design method. The flow field structure and aerodynamic characteristics of osculating flowfield waveriders are also analyzed. In this method, the constraint of imposing the same conical flowfield on each osculating plane is removed because the shock angle of each osculating plane is different, which can be chosen according to the specific needs of waveriders. The obtained results show that the shock angle distribution is an important factor in the design of osculating flowfield waveriders. A waverider whose shock angle increases as a parabolic curve along the spanwise direction has a larger volume and lower lift-to-drag ratio. In contrast, a waverider whose shock angle decreases as a parabolic curve along the spanwise direction has a smaller volume and higher lift-to-drag ratio. Providing different shock angle distributions can lead to greater flexibility in the design and optimization of hypersonic waverider vehicles.
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Acknowledgments
The authors would like to express their gratitude for the financial support provided by the National Natural Science Foundation of China (No. 11702322). The authors are also grateful to the reviewers for their extremely constructive comments.
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Published In
Journal of Aerospace Engineering
Volume 31 • Issue 4 • July 2018
Copyright
©2018 American Society of Civil Engineers.
History
Received: Jul 12, 2017
Accepted: Jan 8, 2018
Published online: May 10, 2018
Published in print: Jul 1, 2018
Discussion open until: Oct 10, 2018
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