The unsteady aerodynamics of the proposed delta planform, high cross range, shuttle orbiters, are investigated. It is found that these vehicles are subject to five unsteady-flow phenomena that could compromise the flight dynamics. The phenomena are as follows: (1) leeside shock-induced separation, (2) sudden leading-edge stall, (3) vortex burst, (4)bow shock-flap shock interaction, and (5) forebody vorticity. Trajectory shaping is seen as the most powerful means of avoiding deterimental effects of the stall phenomena; however, stall must be fixed or controlled when traversing the stall region. Other phenomana may be controlled by carefully programmed control deflections and some configuration modifications. Ways to alter the occurrence of the various flow conditions are explored.


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    Titel :

    Review of delta wing space shuttle vehicle dynamics


    Beteiligte:
    Reding, J. P. (Autor:in) / Ericsson, L. E. (Autor:in)

    Erscheinungsdatum :

    1971-10-01


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Review of delta wing space shuttle vehicle dynamics

    Reding, J. P. / Ericsson, L. E. | NTRS | 1972


    Review of delta Wing Space Shuttle Vehicle Dynamics

    J. P. Reding / L. E. Ericsson | NTIS | 1971


    Delta wing separation can dominate shuttle dynamics.

    Reding, J. P. / Ericsson, L. E. | NTRS | 1972


    Delta wing separation can dominate shuttle dynamics

    REDING, J. / ERICSSON, L. | AIAA | 1972


    Effects of Delta Wing Separation on Shuttle Dynamics

    J. PETER REDING AND LARS E. ERICSSON | AIAA | 1973