NASA's Hyper-X research program was developed primarily to flight demonstrate a supersonic combustion ramjet engine, fully integrated with a forebody designed to tailor inlet flow conditions and a free expansion nozzle/afterbody to produce positive thrust at design flight conditions. With a point-designed propulsion system the vehicle must depend on some other means for boost to its design flight condition. Clean separation from this initial propulsion system stage within less than a second is critical to the success of the flight. This paper discusses the early planning activity, background, and chronology that developed the series of wind-tunnel tests to support multi-degree-of-freedom simulation of the separation process. Representative results from each series of tests are presented, and issues and concerns during the process and current status are highlighted.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Hyper-X Stage Separation Wind-Tunnel Test Program


    Contributors:

    Conference:

    AIAA 18th Applied Aerodynamics Conference ; 2000 ; Denver, CO, United States



    Publication date :

    2001-11-01



    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English


    Keywords :


    Hyper-X Stage Separation Wind-Tunnel Test Program

    William C. Woods / Scott D. Holland / Michael DiFulvio | AIAA | 2001


    Hyper-X Stage Separation Wind Tunnel Test Program

    Woods, W. C. / Holland, S. D. / DiFulvio, M. | NTRS | 2000


    Hyper-X Stage Separation Wind Tunnel Test Program

    W. C. Woods / S. D. Holland / M. DiFulvio | NTIS | 2000



    Hyper-X Storage Separation Wind Tunnel Test Program

    Woods, William C. / Holland, Scott D. / Difulvio, Michael | NTRS | 2000