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 baiss of these data, a semi-empirical LCO prediction method is developed. It is described in its present form and results of the latest predictions will be presented. In particular, an aerodynamic nonlinear state-space model embedded in the LCO prediction mwthod is demonstrated. The developed aerodynamic model is a semi-empirical, unsteady, nonlinear model which uses experimental data obtained from recent unsteady wind tunnel force and pressure measurements on oscillating fighter type wings.


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    Titel :

    Application of Aeroelastic Methods to Predict Flutter Characteristics of Fighter Aircraft in the Transonic Speed Range


    Beteiligte:
    J. J. Meijer (Autor:in)

    Erscheinungsdatum :

    1995


    Format / Umfang :

    19 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Applications of Aeroelastic Methods to Predict Flutter Characteristics of Fighter Aircraft in the Transonic Speed Range

    Meijer, J. J. / Israel Society of Aeronautics and Astronautics | British Library Conference Proceedings | 1995




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    Meijer, J. J. / Nationaal Lucht- en Ruimtevaartlaboratorium | TIBKAT | 1997


    Perspectives of NLR Aeroelastic Methods to Predict Wing/Store Flutter and Dynamic Loads of Fighter Type Aircraft

    Meijer, J.J. / International Council of the Aeronautical Sciences | British Library Conference Proceedings | 2000