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Experimental study of second-mode instability growth and breakdown in a hypersonic boundary layer using high-speed schlieren visualization

Published online by Cambridge University Press:  23 May 2016

S. J. Laurence ,
A. Wagner  and
K. Hannemann
S. J. Laurence*
Affiliation:
Department of Aerospace Engineering, University of Maryland, College Park, MD 20742, USA
A. Wagner
Affiliation:
Institute of Aerodynamics and Flow Technology, Spacecraft Department, German Aerospace Center, Bunsenstraße 10, 37073 Göttingen, Germany
K. Hannemann
Affiliation:
Institute of Aerodynamics and Flow Technology, Spacecraft Department, German Aerospace Center, Bunsenstraße 10, 37073 Göttingen, Germany
*
†Email address for correspondence: stuartl@umd.edu
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Abstract

Visualization experiments are performed to investigate the development of instability waves within the boundary layer on a slender cone under high Mach number conditions. The experimental facility is a reflected-shock wind tunnel, allowing both low (Mach-8 flight equivalent) and high-enthalpy conditions to be simulated. Second-mode instability waves are visualized using a high-speed schlieren set-up, with pulse bursting of the light source allowing the propagation speed of the wavepackets to be unambiguously resolved. This, in combination with wavelength information derived from the images, enables the calculation of the disturbance frequencies. At the lower-enthalpy conditions, we concentrate on the late laminar and transitional regions of the flow. General characteristics are revealed through time-resolved and ensemble-averaged spectra on both smooth and porous ceramic surfaces of the cone. Analysis of the development of individual wavepackets is then performed. It is found that the wavepacket structures evolve from a‘rope-like’ appearance to become more interwoven as the disturbance nears breakdown. The wall-normal disturbance distributions of both the fundamental and first harmonic, which initially have local maxima at the wall and near $y/{\it\delta}=0.7$ –0.75, exhibit an increase in signal energy close to the boundary-layer edge during this evolution. The structure angle of the disturbances also undergoes subtle changes as the wavepacket develops prior to breakdown. Experiments are also performed at high-enthalpy ( $h_{0}\approx 12~\text{MJ}~\text{kg}^{-1}$ ) conditions in the laminar regime, and the visualization technique is shown to be capable of resolving wavepacket propagation speeds and frequencies at such conditions. The visualizations reveal a somewhat different wall-normal distribution to the low-enthalpy case, with the disturbance energy concentrated much more towards the wall. This is attributed to the highly cooled nature of the wall at high enthalpy.

JFM classification

Compressible Flows: Compressible boundary layers Aerodynamics: High-speed flow Instability: Transition to turbulence

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Papers
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Journal of Fluid Mechanics , Volume 797 , 25 June 2016 , pp. 471 - 503
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© 2016 Cambridge University Press 

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