A transonic kernel function method for unsteady flow calculations has been developed. A unified linear pressure panel procedure is established to solve for two-dimensional problems in the subsonic, transonic, and supersonic flow regimes; consequently, a TLP2D computer code is developed. Numerical results are presented for pitching or flapping airfoils in these linear and nonlinear flow regimes. The mixed kernel function procedure is applied to a pitching Guderley airfoil in sonic flow. Comparisons with other results and discussions are given, Additional analytical studies include Landahl's general formulation of the phase correction method and the kernel function formulation of the Eckhaus-Landahl shock-jump model. Finally, assessment of and recommendations for the present work are given. (Jensen)


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    Title :

    Transonic kernel function method for unsteady flow calculations using a unified linear pressure panel procedure


    Additional title:

    Methode zur Berechnung von schallnahen, unstetigen Stroemungen unter Zuhilfenahme eines vereinheitlichten linearen Druckbereichs


    Contributors:
    Liu, D.D. (author) / Pl, W.S. (author) / Landahl, M.T. (author)

    Published in:

    Publication date :

    1979


    Size :

    106 Seiten


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English