An 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
Flow Field Characterization of an Angled Supersonic Jet Near a Bluff Body
28th AIAA Applied Aerodynamics Conference ; 2010 ; Chicago, IL, United States
2011-03-01
Report
Keine Angabe
Englisch
Flow Field Characterization of an Angled Supersonic Jet Near a Bluff Body
British Library Conference Proceedings | 2010
|Turbulent Flow Structure Characterization of Angled injection into a Supersonic Crossflow
Online Contents | 1997
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