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Amplification and structure of streamwise-velocity fluctuations in compression-corner shock-wave/turbulent boundary-layer interactions

Published online by Cambridge University Press:  31 January 2019

M. A. Mustafa Open the ORCID record for M. A. Mustafa [Opens in a new window] ,
N. J. Parziale Open the ORCID record for N. J. Parziale [Opens in a new window] ,
M. S. Smith  and
E. C. Marineau
M. A. Mustafa
Affiliation:
Department of Mechanical Engineering, Stevens Institute of Technology, Hoboken, NJ 07030, USA
N. J. Parziale*
Affiliation:
Department of Mechanical Engineering, Stevens Institute of Technology, Hoboken, NJ 07030, USA
M. S. Smith
Affiliation:
Arnold Engineering Development Complex – White Oak, Silver Spring, MD 20903, USA
E. C. Marineau
Affiliation:
Arnold Engineering Development Complex – White Oak, Silver Spring, MD 20903, USA
*
†Email address for correspondence: nick.parziale@gmail.com
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Abstract

In this work, we study the effect of the compression-corner angle on the streamwise turbulent kinetic energy (sTKE) and structure in Mach 2.8 flow. Krypton tagging velocimetry (KTV) is used to investigate the incoming turbulent boundary layer and flow over $8^{\circ }$, $16^{\circ }$, $24^{\circ }$ and $32^{\circ }$ compression corners. The experiments were performed in a 99 % $\text{N}_{2}$ and 1 % Kr gas mixture in the Arnold Engineering Development Complex (AEDC) Mach 3 Calibration Tunnel (M3CT) at $Re_{\unicode[STIX]{x1D6E9}}=1750$. A figure of merit is defined as the wall-normal integrated sTKE ($\overline{\text{sTKE}}$), which is designed to identify turbulence amplification by accounting for the root-mean-squared (r.m.s.) velocity fluctuations and shear-layer width for the different geometries. We observe that the $\overline{\text{sTKE}}$ increases as an exponential with the compression-corner angle near the root when normalized by the boundary-layer value. Additionally, snapshot proper orthogonal decomposition (POD) is applied to the KTV results to investigate the structure of the flow. From the POD results, we extract the dominant flow structures and compare each case by presenting mean-velocity maps that correspond to the largest positive and negative POD mode coefficients. Finally, the POD spectrum reveals an inertial range common to the boundary-layer and each compression-corner flow that is present after the first ${\approx}10$ dominant POD modes.

JFM classification

Aerodynamics: High-speed flow Compressible Flows: Shock waves Turbulent Flows: Turbulent boundary layers
Type
JFM Papers
Information
Journal of Fluid Mechanics , Volume 863 , 25 March 2019 , pp. 1091 - 1122
Copyright
© Cambridge University Press 2019. This is a work of the U.S. Government and is not subject to copyright protection in the United States. 

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Mustafa et al. supplementary movie 1

8 degree corner instantaneous fluorescence exposures and corresponding velocity profiles.

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Video 6.8 MB

Mustafa et al. supplementary movie 2

16 degree corner instantaneous fluorescence exposures and corresponding velocity profiles.

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Video 6.5 MB

Mustafa et al. supplementary movie 3

24 degree corner instantaneous fluorescence exposures and corresponding velocity profiles.

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Video 6.6 MB

Mustafa et al. supplementary movie 4

32 degree corner instantaneous fluorescence exposures and corresponding velocity profiles.

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Video 7.4 MB