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Laminar hypersonic leading edge separation – a numerical study

Published online by Cambridge University Press:  25 May 2017

Amna Khraibut Open the ORCID record for Amna Khraibut [Opens in a new window] ,
S. L. Gai ,
L. M. Brown  and
A. J. Neely
Amna Khraibut*
Affiliation:
School of Engineering and Information Technology, Northcott Drive, Canberra ACT 2612, Australia
S. L. Gai
Affiliation:
School of Engineering and Information Technology, Northcott Drive, Canberra ACT 2612, Australia
L. M. Brown
Affiliation:
School of Engineering and Information Technology, Northcott Drive, Canberra ACT 2612, Australia
A. J. Neely
Affiliation:
School of Engineering and Information Technology, Northcott Drive, Canberra ACT 2612, Australia
*
†Email address for correspondence: amna.khraibut@student.adfa.edu.au
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Abstract

This paper describes laminar hypersonic leading edge separation. Such a configuration of separated flow was originally studied by Chapman et al. (NACA Tech. Rep. 1356, 1958) at supersonic Mach numbers as it is particularly amenable to theoretical analysis and assumes no pre-existing boundary layer. It can be considered as a limiting case of much studied generic configurations such as separation at a compression corner and separated flow behind a base. A numerical investigation is described using a compressible Navier–Stokes solver assuming perfect gas air, no slip boundary condition and a non-catalytic surface. A moderate enthalpy flow of $3.1\times 10^{6}~\text{J}~\text{kg}^{-1}$ with a unit Reynolds number of $1.34\times 10^{6}~\text{ m}^{-1}$ and a Mach number of 9.66 was considered. The resulting separated flow is analysed in the context of viscous–inviscid interaction and interpreted in terms of ‘triple-deck’ concepts. Particular emphasis is given to wall temperature effects. The effects of strong to moderate wall cooling on flow in the separated region as well as on processes of separation, reattachment and separation length, are highlighted. The numerical simulations have also shown the existence of a secondary eddy embedded within the primary recirculation region, with its size, shape and position, being strongly affected by the wall temperature.

JFM classification

Boundary Layers: Boundary layer separation Mathematical Foundations: Computational methods Aerodynamics: High-speed flow

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Papers
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Journal of Fluid Mechanics , Volume 821 , 25 June 2017 , pp. 624 - 646
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© 2017 Cambridge University Press 

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