Prediction Method of Transonic Limit Cycle Oscillation Characteristics of Fighter Aircraft Using Adapted Steady Wind Tunnel Data
Prediction Method of Transonic Limit Cycle Oscillation Characteristics of Fighter Aircraft Using Adapted Steady Wind Tunnel Data
- Neue Suche nach: J. J. Meijer
- Neue Suche nach: A. M. Cunningham
- Neue Suche nach: J. J. Meijer
- Neue Suche nach: A. M. Cunningham
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 semi-empirical LCO prediction method is being developed. It will be 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 method will be 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.
Dokumentinformationen
Prediction Method of Transonic Limit Cycle Oscillation Characteristics of Fighter Aircraft Using Adapted Steady Wind Tunnel Data
1994
22 pages
Report
Keine Angabe
Englisch
Aircraft , Aerodynamics , Wing oscillations , Transonic flutter , Fighter aircraft , Prediction analysis techniques , Aircraft configurations , Aerodynamic characteristics , Vibration damping , Aeroelasticity , External stores , Pressure distribution , Dynamic models , Time lag , Nonlinearities , Vibration tests , Wind tunnel tests , Foreign technology
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