NDLI: Documentation of two- and three-dimensional hypersonic shock wave/turbulent boundary layer interaction flows

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Documentation of two- and three-dimensional hypersonic shock wave/turbulent boundary layer interaction flows

Content Provider	NASA Technical Reports Server (NTRS)
Author	Kussoy, Marvin I. Horstman, Clifford C.
Copyright Year	1989
Description	Experimental data for a series of two- and three-dimensional shock wave/turbulent boundary layer interaction flows at Mach 7 are presented. Test bodies, composed of simple geometric shapes, were designed to generate flows with varying degrees of pressure gradient, boundary-layer separation, and turning angle. The data include surface-pressure and heat-transfer distributions as well as limited mean-flow-field surveys in both the undisturbed and the interaction regimes. The data are presented in a convenient form for use in validating existing or future computational models of these generic hypersonic flows.
File Size	864168
Page Count	27
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19890010729
Archival Resource Key	ark:/13960/t4vj0fg6q
Language	English
Publisher Date	1989-01-01
Access Restriction	Open
Subject Keyword	Aerodynamics Boundary Layer Separation Shock Waves Aerodynamic Configurations Flow Distribution Wind Tunnel Tests Performance Prediction Turbulent Boundary Layer Wave Interaction Heat Transfer Mach Number Pressure Gradients Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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