Two cases investigated are given length and thickness and given length and enclosed area; indirect methods of calculus of variations are employed, and it is shown that optimum airfoil is diamond shape for case 1 and is biconvex for case 2; if linear theory is employed, maximum lift-to-drag ratio airfoil has maximum thickness at midchord and is symmetric with respect to chord; if nonlinear theory is used, maximum lift-to-drag ratio airfoil has maximum thickness in rear half and is asymmetric with respect to chord (upper contour is thicker than lower contour). (28744)


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Maximum lift-to-drag ratio airfoils at moderate supersonic speeds


    Additional title:

    AIAA J


    Contributors:

    Published in:

    AIAA Journal ; 7 , n 3


    Publication date :

    1969


    Size :

    7 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :