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Aerospace 2017, 4(2), 25; doi:10.3390/aerospace4020025

Assessment of CFD Capability for Hypersonic Shock Wave Laminar Boundary Layer Interactions

Department of Mechanical and Aerospace Engineering, Rutgers—The State University of New Jersey, New Brunswick, NJ 08903, USA
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Author to whom correspondence should be addressed.
Academic Editors: Hossein Zare-Behtash and Kiran Ramesh
Received: 23 December 2016 / Revised: 12 April 2017 / Accepted: 18 April 2017 / Published: 25 April 2017
(This article belongs to the Special Issue Fluid-Structure Interactions)
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Abstract

The goal of this study is to assess CFD capability for the prediction of shock wave laminar boundary layer interactions at hypersonic velocities. More specifically, the flow field over a double-cone configuration is simulated using both perfect gas and non-equilibrium Navier–Stokes models. Computations are compared with recent experimental data obtained from measurements conducted in the LENS XX (Large Energy National Shock Expansion Tunnel Version 2) at the Calspan University of Buffalo Research Center (CUBRC). Four separate cases of freestream conditions are simulated to examine the models for a range of stagnation enthalpies from 5.44 MJ/kg to 21.77 MJ/kg and Mach numbers from 10.9 to 12.82. View Full-Text
Keywords: CFD; hypersonic; shock wave; laminar; real gas; non-equilibrium CFD; hypersonic; shock wave; laminar; real gas; non-equilibrium
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This is an open access article distributed under the Creative Commons Attribution License which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited. (CC BY 4.0).

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Rouhi Youssefi, M.; Knight, D. Assessment of CFD Capability for Hypersonic Shock Wave Laminar Boundary Layer Interactions. Aerospace 2017, 4, 25.

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