Investigation of Flow Control for the Hypersonic Inlets via Counter FlowReport as inadecuate




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International Journal of Aerospace Engineering - Volume 2015 2015, Article ID 956317, 8 pages -

Research ArticleScience and Technology on Scramjet Laboratory, National University of Defense Technology, Changsha 410073, China

Received 1 April 2015; Accepted 4 June 2015

Academic Editor: Linda L. Vahala

Copyright © 2015 Xiaoqiang Fan and Yuan Tao. This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.

Abstract

Experimental results show that there exist two flow fields in the hypersonicinlets when the forebody waves interact with the lip boundary, which is similar to the shock reflection ionhysteresis phenomenon. In order to improve the performance of the flow field, counterflow is appliedto control the shock reflection configuration in the hypersonic inlets. For better understanding of theinternal mechanism, inviscid numerical simulation is conducted. And the results demonstrate that it isfeasible to realize the transition between the regular reflection configuration and the Mach reflection ionconfiguration in the hypersonic inlets. That is because the von Neumann criterion and detachedcriterion play a dominant role, respectively, in these transitions. In addition, the evolution process ofMach reflection ion in the hypersonic inlets can be divided into three stages: transmission of waves,emergence of Mach stem, and stabilization of flow field.





Author: Xiaoqiang Fan and Yuan Tao

Source: https://www.hindawi.com/



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