A model for determining aerodynamic loads from steady and unsteady databases is presented that is suitable for predicting Limit Cycle Oscillations (LCO) of fighter aircraft at transonic speeds. Validations of the model are presented, in particular the influence of Mach number variations, different control flap settings and oscillation frequency and amplitude are demonstrated. A few examples of the aerodynamic model embedded in the LCO prediction method are presented to show the LCO characteristics of a fighter type aircraft. Finally, enhancement of the use of the model are discussed by extension of the data bases with data obtained from CFD methods and/or new wind tunnel experiments.
Determination of Transonic Unsteady Aerodynamic Loads to Predict the Aeroelastic Stability of Fighter Aircraft
1997
18 pages
Report
No indication
English
Aerodynamics , Aircraft , Figher aircraft , Aeroelasticity , Aerodynamic loads , External stores , Wing flaps , Wing oscillations , Pressure distribution , Transonic flutter , Vibration damping , Hysteresis , Nonlinearities , Prediction analysis techniques , Parameter identification , Time lag , Dynamic models , Mach number , Foreign technology