A method is developed consistent with the assumptions of small perturbation theory which provides a means of determining the downwash behind a wing in supersonic flow for a known load distribution. The analysis is based upon the use of supersonic doublets which are distributed over the plan form and wake of the wing in a manner determined from the wing loading. The equivalence in subsonic and supersonic flow of the downwash at infinity corresponding to a given load distribution is proved.


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    Title :

    The calculation of downwash behind supersonic wings with an application to triangular plan forms


    Contributors:

    Publication date :

    1950-01-01


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English