Limitations concerning the possibility to simulate all the significant flow and thermal phenomena occurring during the entry of a space vehicle into a planetary atmosphere make it necessary to rely on computational analyses to obtain the required data for the design of the spacecraft needed for the NASA missions planned for the next two decades. 'Benchmark' computer programs concerned with complete, detailed, and accurate computational solutions of entry problems are considered along with programs representing engineering approximations for cases in which the accuracy provided by the benchmark programs is not needed. The information obtainable by computational analysis has to be supplemented by actual flight experience in order to meet the goals of the NASA entry-technology program. The individual space missions planned for the coming years are examined together with the possibilities for obtaining the data needed to satisfy the entry requirements in each case.


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    Titel :

    Planetary entry aerothermodynamics. II - Computational analyses and flight experience


    Beteiligte:
    Olstad, W. B. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    01.12.1974


    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Aerothermodynamics and planetary entry : Technical papers

    American Institute of Aeronautics and Astronautics / Aerospace Sciences Meeting / Thermophysics Conference | TIBKAT | 1981




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    Entry Trajectory Aerothermodynamics of Space Vehicles in Planetary Atmospheres

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