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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    Titel :

    Nonlinear airfoil theory for rectangular wings in compressible flow


    Weitere Titelangaben:

    NASA -- Report


    Beteiligte:
    Gersten, K. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    1959


    Format / Umfang :

    14 pages


    Medientyp :

    Report


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :


    Calculating derivatives for rectangular wings oscillating in compressible subsonic flow

    Lehrian, Doris E. / Aeronautical Research Council | TIBKAT | 1958




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    Durmuş, G / Kavsaoğlu, M Ş / Kaynak, Ü | SAGE Publications | 2011


    Parallel Solution of Low Aspect Ratio Rectangular Flat Wings in Compressible Flow

    Durmus, G. / Kavsaoglu, M. S. / Kaynak, U. et al. | British Library Conference Proceedings | 2005