Above certain Mach numbers, flows in wind tunnels can no longer fully simulate the actual flow physics. In the design of optimal propulsion systems, which are capable of economically propelling aircraft to hypersonic Mach numbers, understanding of the 'real' flow is mandatory. This paper will address recently developed numerical elements of an advanced CFD code in terms of computational speed and accuracy. Results will be presented of several calculations performed to gain insight into the flow in hypersonic intakes.


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    Titel :

    CFD Contributions During Hypersonic Airplane Intake Design


    Beteiligte:
    N. C. Bissinger (Autor:in) / A. Eberle (Autor:in)

    Erscheinungsdatum :

    1992


    Format / Umfang :

    24 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




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    N. C. Bissinger / A. Eberle | NTIS | 1991


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