Next Article in Journal
Development of Hollow Cathodes for Space Electric Propulsion at Sitael
Previous Article in Journal
Effects of Wake Shapes on High-Lift System Aerodynamic Predictions
Previous Article in Special Issue
Control of Triple-Shock Configurations and Vortex Structures Forming in High Speed Flows of Gaseous Media past an AD Body under the Action of External Energy Sources
Article Menu
Issue 2 (June) cover image

Export Article

Open AccessArticle
Aerospace 2017, 4(2), 25;

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
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)
Full-Text   |   PDF [6675 KB, uploaded 25 April 2017]   |  


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

Figure 1

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).

Share & Cite This Article

MDPI and ACS Style

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

Show more citation formats Show less citations formats

Note that from the first issue of 2016, MDPI journals use article numbers instead of page numbers. See further details here.

Related Articles

Article Metrics

Article Access Statistics



[Return to top]
Aerospace EISSN 2226-4310 Published by MDPI AG, Basel, Switzerland RSS E-Mail Table of Contents Alert
Back to Top