Method for calculating theoretical pressure distribution over large class of flat wings at angle of attack, for Mach numbers greater than 1.0; formulas are worked out in detail for moderately and highly swept wings of arbitrary taper, and include formulas for integrated lift, pitching moment, and induced drag.


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    Title :

    Theoretical lift of flat swept-back wings at supersonic speeds


    Additional title:

    Nat Advisory Committee Aeronautics -- Tech Note


    Contributors:
    Cohen, D. (author)


    Publication date :

    1948


    Size :

    57 pages


    Remarks:

    20 Supp plates, Bibliography


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :