An analysis of steady wind tunnel data, obtained for a fighter type aircraft, has indicated that shock induced and trailing edge separation play a dominant role in the development of limit cycle oscillations (LCO) at transonic speeds. On the basis of these data, a semiempirical LCO prediction method is being developed. Its preliminary version was applied to several configurations and correctly identified those which have encountered LCO. It has already shown the potential for application early in the design process of new aircraft to determine and understand the nonlinear aeroelastic characteristics. An upgraded form is described and results of the latest predictions are used to further assess various parametric effects. The ultimate refinements are expected from unsteady wind tunnel force and pressure measurements for which preliminary results are presented.


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    Titel :

    Understanding and Development of a Prediction Method of Transonic Limit Cycle Oscillation Characteristics of Fighter Aircraft


    Beteiligte:
    J. J. Meijer (Autor:in) / A. M. Cunningham (Autor:in)

    Erscheinungsdatum :

    1992


    Format / Umfang :

    17 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch