Pressure and gauge wind tunnel data from a transonic test of a 0.02 scale model of the space shuttle launch vehicle was analyzed to define the aerodynamic influence of the main propulsion system and solid rocket booster plumes during the transonic portion of ascent flight. Air was used as a simulant gas to develop the model exhaust plumes. A math model of the plume induced aerodynamic characteristics was developed for a range of Mach numbers to match the forebody aerodynamic math model. The base aerodynamic characteristics are presented in terms of forces and moments versus attitude. Total vehicle base and forebody aerodynamic characteristics are presented in terms of aerodynamic coefficients for Mach number from 0.6 to 1.4 Element and component base and forebody aerodynamic characteristics are presented for Mach numbers of 0.6, 1.05, 1.1, 1.25 and 1.4. The forebody data is available at Mach 1.55. Tolerances for all plume induced aerodynamic characteristics are developed in terms of a math model.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Space Shuttle Plume Simulation Application. Results and Math Model


    Contributors:
    W. Boyle (author) / B. Conine (author)

    Publication date :

    1978


    Size :

    209 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English







    Space shuttle plume/simulation application

    Boyle, W. / Conine, B. / Bell, G. | NTRS | 1979


    Space Shuttle Plume/Simulation Application

    W. Boyle / B. Conine / G. Bell | NTIS | 1979