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Experiments on the mechanism of inducing transition between regular and Mach reflection

Phys. Fluids 20, 126103 (2008); doi:10.1063/1.3042261

Published 18 December 2008

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Christopher A. Mouton and Hans G. Hornung
Graduate Aeronautical Laboratories, California Institute of Technology, 1200 East California Boulevard, MC 105-50, Pasadena, California 91125, USA
A study of the mechanism by which disturbances can cause tripping between steady-flow regular and Mach reflection in the dual-solution domain is presented. Computational results indicate that the disturbance shock created as a result of the impact of dense particles on one of the shock-generating wedges can cause transition from regular to Mach reflection. The disturbance shock may also be generated by direct energy deposition on the wedge. Estimates of the lower bound of the required energy for transition to occur are presented and compared to values obtained computationally. Experiments were performed at Mach 4.0 in a Ludwieg tube that has a test duration of 100 ms. Proper starting of the flow necessitated operation with an upstream diaphragm and modifications in the dump tank. The reflection state was changed by rapid rotation of one of the shock-generating wedges. The flow in the facility is sufficiently quiet to permit entering the dual-solution domain to approximately its midpoint before spontaneous transition to the Mach reflection occurs. The short test time prompted a study of the effect of wedge rotation speed on the transition from regular to Mach reflection. Transition due to deposition of energy on one of the wedges was also examined by using a pulsed laser focused on one of the two wedges. Measurements of the minimum energy to bring about transition and of the rapid growth of the Mach stem to its steady-state are compared to numerical and theoretical predictions. ©2008 American Institute of Physics
History: Received 15 July 2008; accepted 7 November 2008; published 18 December 2008
Permalink: http://link.aip.org/link/?PHFLE6/20/126103/1
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KEYWORDS and PACS

Keywords
PACS
  • 47.40.Nm
    Shock-wave interactions and shock effects
  • 47.40.Ki
    Supersonic and hypersonic flows
  • YEAR: 2008

PUBLICATION DATA

ISSN:
1070-6631 (print)   1089-7666 (online)
Publisher:
AIP is a member of CrossRef AIP

REFERENCES (12)
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