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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    Title :

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


    Contributors:

    Publication date :

    1995


    Size :

    19 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English