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Modification impact on aerodynamic performance of hypersonic waverider

Published online by Cambridge University Press:  27 January 2016

C. Xiao-Qing ,
H. Zhong-Xi ,
L. Jian-Xia  and
G. Xian-Zhong
H. Zhong-Xi
Affiliation:
College of Aerospace and Materials Engineering, National University of Defense Technology, Changsha, China
L. Jian-Xia
Affiliation:
College of Aerospace and Materials Engineering, National University of Defense Technology, Changsha, China
G. Xian-Zhong
Affiliation:
College of Aerospace and Materials Engineering, National University of Defense Technology, Changsha, China
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Abstract

Waverider serves as a good candidate for hypersonic vehicles. The typical waverider has sharp leading edge and no control face, which is inappropriate for practical use. This paper puts forward a method modifying the waverider, and the modification impact on the performance of waverider at hypersonic flow conditions is studied. The modification is based on blunted waverider, includes cutting the tip and introducing two control wings. The modification’s effect on aerodynamic performance is obtained and analysed through Computational Fluid Dynamics (CFD) techniques. When blunted with 2cm radius, the waverider retains its good aerodynamic performance and the heat flux at the stagnation point can be managed. Three factors of the introduced wing are argued, the fixed angle, aspect ratio and wing area. Results show that influence on the aerodynamic coefficient is slight and the vehicle retains its high lift-to-drag ratio. The main influences of the modification are the control ability and trim efficiency, which is the motivation of this work and can be adapted when designing a practical waverider.

Type
Research Article
Information
The Aeronautical Journal , Volume 115 , Issue 1168 , June 2011 , pp. 325 - 334
Copyright
Copyright © Royal Aeronautical Society 2011 

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