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.


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    Title :

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


    Contributors:
    S. Xu (author)

    Publication date :

    1987


    Size :

    17 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English





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