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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. The results will serve to define the region of interest where more detailed mean and turbulence measurements will be made.
Document ID
20150015493
Acquisition Source
Glenn Research Center
Document Type
Conference Paper
Authors
Davis, David O. (NASA Glenn Research Center Cleveland, OH United States)
Date Acquired
August 6, 2015
Publication Date
July 26, 2015
Subject Category
Fluid Mechanics And Thermodynamics
Report/Patent Number
AJK2015-06342
GRC-E-DAA-TN23733
Report Number: AJK2015-06342
Report Number: GRC-E-DAA-TN23733
Meeting Information
Meeting: 2015 AJK Fluids Engineering Division Summer Meeting
Location: Seoul
Country: Korea, Republic of
Start Date: July 26, 2015
End Date: July 31, 2015
Sponsors: American Society of Mechanical Engineers, Japan Society of Mechanical Engineers
Funding Number(s)
WBS: WBS 109492.02.03.01.01.01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
Superonic Flow
Turbulence Modeling
Shock-Wave/Boundary Layer Interaction

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