The NASA X-43 'Hyper-X' hypersonic research vehicle will be boosted to a Mach 7 flight test condition mounted on the nose of an Orbital Sciences Pegasus launch vehicle. The separation of the research vehicle from the Pegasus presents some unique aerodynamic problems, for which computational fluid dynamics has played a role in the analysis. This paper describes the use of several CFD methods for investigating the aerodynamics of the research and launch vehicles in close proximity. Specifically addressed are unsteady effects, aerodynamic database extrapolation, and differences between wind tunnel and flight environments.


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    Title :

    Prediction of Hyper-X Stage Separation Aerodynamics Using CFD


    Contributors:
    P. G. Buning (author) / T. C. Wong (author) / A. D. Dilley (author) / J. L. Pao (author)

    Publication date :

    2000


    Size :

    12 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    Prediction of Hyper-X Stage Separation Aerodynamics Using CFD

    Buning, Pieter G. / Wong, Tin-Chee / Dilley, Arthur D. et al. | NTRS | 2000


    Prediction of Hyper-X stage separation aerodynamics using CFD

    Buning, Pieter / Wong, Tin-Chee / Dilley, Arthur et al. | AIAA | 2000


    Computational Fluid Dynamics Prediction of Hyper-X Stage Separation Aerodynamics

    Pieter G. Buning / Tin-Chee Wong / Arthur D. Dilley et al. | AIAA | 2001