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.
Application of Aeroelastic Methods to Predict Flutter Characteristics of Fighter Aircraft in the Transonic Speed Range
1995
19 pages
Report
No indication
English
Aircraft , Aerodynamics , Aeroelasticity , Transonic flutter , Fighter aircraft , Aircraft configurations , Wing oscillations , Trailing edges , Separated flow , Dampling , Pressure distribution , Time marching , Unsteady aerodynamics , Prediction analysis techniques , Unsteady flow , Wind tunnel tests , Foreign technology
British Library Conference Proceedings | 1995
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