A series of parametric wind tunnel tests was conducted to provide a base for developing a simulation of afterbody/base aerodynamics for multibody/multibase rocket-powered vehicles (such as Space Shuttle) which use unheated air as the simulant gas in development wind tunnel tests. The tests described were parameterized on external configuration, nozzle internal configuration, base geometry, propulsion gas type, and freestream Mach number (0.5 to 3.5). The tests were conducted over a 4-year period. Presented in this report are the data and pertinent reference information necessary to perform an analysis which would lead to a simulation procedure. The type of data obtained during the tests described herein include model base afterbody, and nozzle internal surface static pressure distributions, model chamber pressure and temperature, and freestream conditions. Also included is a brief description of simulation procedures that were used by the Space Shuttle program.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Space Shuttle Afterbody Aerodynamics/Plume Simulation Data Summary


    Contributors:

    Publication date :

    1978


    Size :

    195 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English





    Space shuttle afterbody aerodynamic/plume simulation data summary

    Blackwell, Kenneth L. / Hair, Leroy M. | TIBKAT | 1978



    Aerodynamics of aircraft afterbody

    NATO, Working Group on Aerodynamics of Aircraft Afterbody | TIBKAT | 1986