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CFD Validation Experiment of a Mach 2.5 Axisymmetric Shock-Wave/Boundary-Layer Interaction

[+] Author Affiliations
David O. Davis

NASA Glenn Research Center, Cleveland, OH

Paper No. AJKFluids2015-6342, pp. V001T06A001; 11 pages
  • ASME/JSME/KSME 2015 Joint Fluids Engineering Conference
  • Volume 1: Symposia
  • Seoul, South Korea, July 26–31, 2015
  • Conference Sponsors: Fluids Engineering Division
  • ISBN: 978-0-7918-5721-2


Preliminary 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.



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