The finite element method is used to calculate the spanwise variation of potential form drag of a wing at subsonic and supersonic speeds using linearly varying panels. The wing may be of arbitrary planform and nonplanar provided the wing panels are parallel to the aircraft axis.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Spanwise variation of potential form drag


    Contributors:

    Publication date :

    1977-05-18


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English


    Keywords :