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Flow Field Characterization of an Angled Supersonic Jet Near a Bluff BodyAn experiment was performed to acquire data from a hot supersonic jet in cross flow for the purpose of validating computational fluid dynamics (CFD) turbulence modeling relevant to the Orion Launch Abort System. Hot jet conditions were at the highest temperature and pressure that could be acquired in the test facility. The nozzle pressure ratio was 28.5, and the nozzle temperature ratio was 3. These conditions are different from those of the flight vehicle, but sufficiently high to model the observed turbulence features. Stereo Particle Image Velocimetry (SPIV) data and capsule pressure data are presented. Features of the flow field are presented and discussed
Document ID
20110010204
Acquisition Source
Glenn Research Center
Document Type
Technical Memorandum (TM)
Authors
Wolter, John D. (NASA Glenn Research Center Cleveland, OH, United States)
Childs, Robert (Eloret Corp. Moffett Field, CA, United States)
Wernet, Mark P. (NASA Glenn Research Center Cleveland, OH, United States)
Shestopalov, Andrea (Eloret Corp. Moffett Field, CA, United States)
Melton, John E. (NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
August 25, 2013
Publication Date
March 1, 2011
Subject Category
Aerodynamics
Report/Patent Number
E-17563
NASA/TM-2011-216958
AIAA Paper 2010-4829
Meeting Information
Meeting: 28th AIAA Applied Aerodynamics Conference
Location: Chicago, IL
Country: United States
Start Date: June 28, 2010
End Date: July 1, 2010
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
WBS: WBS 644423.02.39.03.02
Distribution Limits
Public
Copyright
Public Use Permitted.

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