Structure of supersonic turbulent flow past a swept compression corner

Doyle Knight, C. C. Horstman

Research output: Contribution to journalArticle

13 Scopus citations

Abstract

The structure of the shock wave/turbulent boundary-layer interaction generated by a three-dimensional swept compression corner has been investigated through a combined experimental and theoretical research program. The flowfield geometry is defined by the streamwise compression angle a. and the sweep angle μ of the corner. The present study examines two different configurations, namely, (α, μ) = (24 deg, 40 deg) and (24 deg, 60 deg) at Mach 3 and Reδα ≈ 9 × 105. The theoretical model is the three-dimensional Reynolds-averaged compressible Navier-Stokes equations with turbulence incorporated using a turbulent eddy viscosity. Four different turbulence models (Baldwin-Lomax, Cebeci-Smith, Jones-Launder with wall functions, and Jones-Launder integrated to the wall) were employed. The calculated flowfields display general agreement with experimental data for surface pressure and good agreement with experimental flowfield profiles of pitot pressure and yaw angle. The principal feature of the flowfield is a large vortical structure approximately aligned with the corner. The entrainment of incoming fluid into the vortical structure is strongly affected by the sweep angle μ. Viscous (turbulent and molecular) effects appear to be important only in the immediate vicinity of the surface and in an isolated region within the interaction and near the corner.

Original languageEnglish (US)
Pages (from-to)890-896
Number of pages7
JournalAIAA journal
Volume30
Issue number4
DOIs
StatePublished - Jan 1 1992

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering

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