A method for calculating aerodynamic heat transfer on thin wings at angles of attack is provided, based on the assumption of small cross flow and the calculation of an infinite cylinder. It is valid in the range of supersonic and hypersonic speeds. The method does not require calculation of the details of the stream lines and can be used for various swept wings at moderate angle of attack or yaw angle. A comparison between theoretical and experimental results is given.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Calculation of Aerodynamic Heat Transfer for Blunt-Nosed Thin Wings at Different Angles of Attack at Supersonic Speeds


    Beteiligte:
    S. Xu (Autor:in)

    Erscheinungsdatum :

    1987


    Format / Umfang :

    17 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch