Applying simple extension of conventional concept of vortex system of linear airfoil theory, nonlinear dependence of aerodynamic coefficients on angle of attack can be given; computation carried out by means of system of equations, based on linear theory. English translation from Zeit fuer Flugwissenschaften, Sept 1957, indexed in Engineering Index 1957 p 57 under Aircraft Wings.


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    Title :

    Nonlinear airfoil theory for rectangular wings in compressible flow


    Additional title:

    NASA -- Report


    Contributors:
    Gersten, K. (author)

    Published in:

    Publication date :

    1959


    Size :

    14 pages


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English


    Keywords :