Simulation of hypersonic shock wave/boundary layer interaction using high order WENO scheme

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

3 Scopus citations

Abstract

This paper investigates the accuracy and robustness of high order WENO schemes for predicting hypersonic shock wave/boundary layer interaction. The implicit time marching method with unfactored Gauss-Seidel line relaxation is used with a 5th order WENO finite difference scheme for inviscid fluxes. The viscous terms are discretized using a 4th order conservative central differencing. Numerical results agree well with the experiment of a hollow/flare geometry at Mach number of 12.49 and Reynolds number of 1.09 × 10 5/ft.

Original languageEnglish (US)
Title of host publication48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition
PublisherAmerican Institute of Aeronautics and Astronautics Inc.
ISBN (Print)9781600867392
DOIs
StatePublished - 2010

Publication series

Name48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

ASJC Scopus subject areas

  • Aerospace Engineering

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    Shen, Y., Zha, G., & Huerta, M. A. (2010). Simulation of hypersonic shock wave/boundary layer interaction using high order WENO scheme. In 48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition [2010-1047] (48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition). American Institute of Aeronautics and Astronautics Inc.. https://doi.org/10.2514/6.2010-1047