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CFD Validation Experiment of a Mach 2.5 Axisymmetric Shock-Wave/Boundary-Layer InteractionPreliminary results of an experimental investigation of a Mach 2.5 two-dimensional axisymmetric shock-wave/ boundary-layer interaction (SWBLI) are presented. The purpose of the investigation is to create a SWBLI dataset specifically for CFD validation purposes. Presented herein are the details of the facility and preliminary measurements characterizing the facility and interaction region. These results will serve to define the region of interest where more detailed mean and turbulence measurements will be made.
Document ID
20150021042
Document Type
Technical Memorandum (TM)
Authors
Davis, David Owen (NASA Glenn Research Center Cleveland, OH United States)
Date Acquired
November 10, 2015
Publication Date
September 1, 2015
Subject Category
Fluid Mechanics And Thermodynamics
Report/Patent Number
GRC-E-DAA-TN23467
AJK2015-06342
NASA/TM-2015-218841
Meeting Information
Joint Fluids Engineering Conference 2015(Seoul)
Funding Number(s)
WBS: WBS 109492.02.03.01.01.01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
Shock-Wave/Boundary Layer Interaction
Superonic Flow
Turbulence Modeling

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