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


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Flow Field Characterization of an Angled Supersonic Jet Near a Bluff Body


    Contributors:

    Conference:

    28th AIAA Applied Aerodynamics Conference ; 2010 ; Chicago, IL, United States


    Publication date :

    2011-03-01


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English


    Keywords :


    Flow Field Characterization of an Angled Supersonic Jet Near a Bluff Body

    Wolter, John / Childs, Robert / Wernet, Mark et al. | AIAA | 2010


    Flow Field Characterization of an Angled Supersonic Jet Near a Bluff Body

    Wolter, J. / Childs, R. / Wernet, M. et al. | British Library Conference Proceedings | 2010