Shock Wave Laminar Boundary Layer Interaction over a Double Wedge in a high mach Number Flow

Mohammad A. Badr, Doyle D. Knight

Research output: Chapter in Book/Report/Conference proceedingConference contribution

4 Scopus citations

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.

Original languageEnglish (US)
Title of host publication52nd Aerospace Sciences Meeting
PublisherAmerican Institute of Aeronautics and Astronautics Inc.
ISBN (Electronic)9781624102561
DOIs
StatePublished - 2014
Externally publishedYes
Event52nd Aerospace Sciences Meeting 2014 - National Harbor, United States
Duration: Jan 13 2014Jan 17 2014

Publication series

Name52nd Aerospace Sciences Meeting

Conference

Conference52nd Aerospace Sciences Meeting 2014
Country/TerritoryUnited States
CityNational Harbor
Period1/13/141/17/14

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering

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