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Direct simulation Monte Carlo computations and experiments on leading-edge separation in rarefied hypersonic flow

Published online by Cambridge University Press:  02 October 2019

R. Prakash Open the ORCID record for R. Prakash [Opens in a new window] ,
L. M. Le Page Open the ORCID record for L. M. Le Page [Opens in a new window] ,
L. P. McQuellin Open the ORCID record for L. P. McQuellin [Opens in a new window] ,
S. L. Gai Open the ORCID record for S. L. Gai [Opens in a new window]  and
S. O’Byrne Open the ORCID record for S. O’Byrne [Opens in a new window]
R. Prakash*
Affiliation:
School of Engineering and Information Technology, University of New South Wales, Canberra, ACT 2612, Australia
L. M. Le Page
Affiliation:
School of Engineering and Information Technology, University of New South Wales, Canberra, ACT 2612, Australia
L. P. McQuellin
Affiliation:
School of Engineering and Information Technology, University of New South Wales, Canberra, ACT 2612, Australia
S. L. Gai
Affiliation:
School of Engineering and Information Technology, University of New South Wales, Canberra, ACT 2612, Australia
S. O’Byrne
Affiliation:
School of Engineering and Information Technology, University of New South Wales, Canberra, ACT 2612, Australia
*
†Email address for correspondence: ram.prakash@student.adfa.edu.au
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Abstract

A comprehensive study of the fundamental characteristics of leading-edge separation in rarefied hypersonic flows is undertaken and its salient features are elucidated. Separation of a boundary layer undergoing strong expansion is typical in many practical hypersonic applications such as base flows of re-entry vehicles and flows over deflected control surfaces. Boundary layer growth under such conditions is influenced by effects of rarefaction and thermal non-equilibrium, thereby differing significantly from the conventional no-slip Blasius type. A leading-edge separation configuration presents a fundamental case for studying the characteristics of such a flow separation but with minimal influence from a pre-existing boundary layer. In this work, direct simulation Monte Carlo computations have been performed to investigate flow separation and reattachment in a low-density hypersonic flow over such a configuration. Distinct features of leading-edge flow, limited boundary layer growth, separation, shear layer, flow structure in the recirculation region and reattachment are all explained in detail. The fully numerical shear layer profile after separation is compared against a semi-theoretical profile, which is obtained using the numerical separation profile as the initial condition on existing theoretical concepts of shear layer analysis based on continuum flow separation. Experimental studies have been carried out to determine the surface heat flux using thin-film gauges and computations showed good agreement with the experimental data. Flow visualisation experiments using the non-intrusive planar laser-induced fluorescence technique have been performed to image the fluorescence of nitric oxide, from which velocity and rotational temperature distributions of the separated flow region are determined.

JFM classification

Aerodynamics: High-speed flow Wakes/Jets: Separated flows Rarefied Gas Flow: Rarefied Gas Flow

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JFM Papers
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Journal of Fluid Mechanics , Volume 879 , 25 November 2019 , pp. 633 - 681
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© 2019 Cambridge University Press 

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