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A study of the asymmetric shock reflection configurations in steady flows

Published online by Cambridge University Press:  18 July 2017

Yuan Tao
Affiliation:
Science and Technology on Scramjet Laboratory, National University of Defense Technology, Changsha, 410073, PR China
Weidong Liu*
Affiliation:
Science and Technology on Scramjet Laboratory, National University of Defense Technology, Changsha, 410073, PR China
Xiaoqiang Fan
Affiliation:
Science and Technology on Scramjet Laboratory, National University of Defense Technology, Changsha, 410073, PR China
Bin Xiong
Affiliation:
Science and Technology on Scramjet Laboratory, National University of Defense Technology, Changsha, 410073, PR China
Jiangfei Yu
Affiliation:
College of Aerospace Science and Engineering, National University of Defense Technology, Changsha, 410073, PR China
Mingbo Sun
Affiliation:
Science and Technology on Scramjet Laboratory, National University of Defense Technology, Changsha, 410073, PR China
*
Email address for correspondence: WDliu@nudt.edu.cn

Abstract

In this paper the asymmetric shock reflection configurations in two-dimensional steady flows have been studied theoretically. For an overall Mach reflection, it is found that the horizontal distance between both triple points in the Mach stem is related to the angles of two slip streams. Based on the features of the converging stream tube, several assumptions are put forward to perform better the wave configurations near the slip streams. Therefore, we present an analytical model here to describe the asymmetric overall Mach reflection configurations which agrees well with the computational and experimental results.

Type
Papers
Copyright
© 2017 Cambridge University Press 

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