@inproceedings{ebaa63d52a07413b828282c300564ffb,
title = "Shock Wave Laminar Boundary Layer Interaction over a Double Wedge in a high mach Number Flow",
abstract = "Shock wave laminar boundary layer interaction (SWBLI) over a double wedge at Mach 7.14 and 7.11 were simulated using the commercial ow solver GASPex. An inviscid sim-ulation was performed at Mach 7.14 for validation. Results for the region downstream of the_rst shock wave show less than one percent error in comparison with oblique shock wave theory. Laminar perfect gas simulations were performed for stagnation enthalpies of 2 MJ/kg and 8 MJ/kg. The computed heat transfer distribution agrees closely with the experiment upstream of the shock wave laminar boundary layer interaction; however, signi_cant di_erences are evident in the region of the interaction. In particular, the time-accurate simulations indicate a signi_cantly longer physical time to achieve steady state than observed in the experiment.",
author = "Badr, {Mohammad A.} and Knight, {Doyle D.}",
note = "Publisher Copyright: {\textcopyright} 2015 American Institute of Aeronautics and Astronautics Inc. All rights reserved.; 52nd Aerospace Sciences Meeting 2014 ; Conference date: 13-01-2014 Through 17-01-2014",
year = "2014",
doi = "10.2514/6.2014-1136",
language = "English (US)",
series = "52nd Aerospace Sciences Meeting",
publisher = "American Institute of Aeronautics and Astronautics Inc.",
booktitle = "52nd Aerospace Sciences Meeting",
}