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Crossflow instability in a hypersonic boundary layer

Published online by Cambridge University Press:  27 October 2016

Stuart A. Craig*
Affiliation:
Department of Aerospace & Mechanical Engineering, University of Arizona, Tucson, AZ 85721, USA Department of Aerospace Engineering, Texas A&M University, College Station, TX 77843, USA
William S. Saric
Affiliation:
Department of Aerospace Engineering, Texas A&M University, College Station, TX 77843, USA
*
Email address for correspondence: sacraig@email.arizona.edu

Abstract

The crossflow instability in a hypersonic, laminar boundary layer is investigated using point measurements inside the boundary layer for the first time. Experiments are performed on a 7° right, circular cone with an adiabatic wall condition at 5.6° angle of incidence in the low-disturbance Mach 6 Quiet Tunnel at Texas A&M University. Measurements are made with a constant-temperature hot-wire anemometer system with a frequency response up to 180 kHz. Stationary crossflow waves are observed to grow and saturate. A travelling wave coexists with the stationary wave and occurs in a frequency band centred around 35 kHz. A type-I secondary instability is also observed in a frequency band centred around 110 kHz. The behaviour of all three modes is largely consistent with their low-speed counterparts prior to saturation of the stationary wave. Afterward, the behaviour remains in partial agreement with the low-speed case. Neither type-II secondary instability nor transition to turbulence are observed in this study.

Type
Papers
Copyright
© Cambridge University Press 2016. This is a work of the U.S. Government and is not subject to copyright protection in the United States. 

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