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Wall temperature and bluntness effects on hypersonic laminar separation at a compression corner

Published online by Cambridge University Press:  02 July 2021

D. Exposito Open the ORCID record for D. Exposito [Opens in a new window] ,
S.L. Gai Open the ORCID record for S.L. Gai [Opens in a new window]  and
A.J. Neely Open the ORCID record for A.J. Neely [Opens in a new window]
D. Exposito*
Affiliation:
School of Engineering and Information Technology, University of New South Wales, Canberra, ACT2612, Australia
S.L. Gai
Affiliation:
School of Engineering and Information Technology, University of New South Wales, Canberra, ACT2612, Australia
A.J. Neely
Affiliation:
School of Engineering and Information Technology, University of New South Wales, Canberra, ACT2612, Australia
*
†Email address for correspondence: [email protected]
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Abstract

This paper describes a numerical investigation on the effects of wall temperature and leading-edge bluntness on hypersonic laminar separation induced by a finite-span compression corner. The flow conditions were: Mach number 9.66; Reynolds number $1.34 \times 10^6$ per metre; and stagnation temperature 3150 K. The wall to stagnation temperature ratio ($s_w$) varied from 0.095 to 0.333 and was thus in the subcritical range as per the classification of Brown et al. (J. Fluid Mech., vol. 220, 1990, pp. 309–337). Two leading-edge bluntnesses of $40\ \mathrm {\mu }\textrm {m}$ and $200\ \mathrm {\mu }\textrm {m}$ were used in the investigation. Numerical solutions were obtained using a compressible Navier–Stokes solver and compared with triple-deck solutions obtained using the numerical method of Cassel et al. (J. Fluid Mech., vol. 300, 1995, pp. 265–285). Separation was induced by ramp angles of $10^{\circ }$ and $20^{\circ }$, which produced near incipient and large separations. The scaled angles, which increased with wall to stagnation temperature ratio, were not sufficient to induce secondary separation in the main recirculation region. Two regimes of shock interference were identified depending on the wall temperature ratio. The corner instability in the form of a stationary wave-packet identified by Cassel et al. (J. Fluid Mech., vol. 300, 1995, pp. 265–285) for scaled angles $\alpha \geq 3.9$ was investigated but is shown to be a numerical artefact of the algorithm rather than having any physical basis. Increasing both the wall temperature ratio and blunting increased the separation length. And there is an equivalence between cooling the wall and reducing bluntness both leading to a reduced separation length.

JFM classification

Aerodynamics: High-speed flow Boundary Layers: Boundary layer separation Compressible Flows: Hypersonic Flow
Type
JFM Papers
Information
Journal of Fluid Mechanics , Volume 922 , 10 September 2021 , A1
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Copyright
© The Author(s), 2021. Published by Cambridge University Press

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