Requirements of modern fighter aircraft to operate with high maneuverability in the transonic speed regime may lead under certain conditions to limit cycle oscillations (LCO), produced by a structural/aerodynamic interaction. Conditions of transonic LCO are moderate angle of attack and Mach numbers ranging from 0.9 to 1.1. An analysis of steady wind tunnel data, obtained for a fighter type aircraft in a typical configuration, has indicated that shock-induced separation plays a dominant role. In the paper, a semi-empirical prediction method is presented which makes use of these steady data, and some results are shown. Possibilities are discussed to extend the method to the use of unsteady wind tunnel data.
Investigation of a Semi-Empirical Method to Predict Limit Cycle Oscillations of Modern Fighter Aircraft (Meeting Paper)
1990
29 pages
Report
No indication
English
Aerodynamics , Aircraft , Dynamic response , Fighter aircraft , Cyclic loads , Fatigue limit , Transonic flow , Mathematical models , Wind tunnel tests , Vibration damping , Structural vibration , Oscillations , Flutter , Unsteady flow , Angle of attack , Mach number , Aerodynamic stability , Foreign technology
Higher-Order Spectral Analysis of Limit Cycle Oscillations of Fighter Aircraft
Online Contents | 2008
|MATHEMATICAL MODELS FOR THE PREDICTION OF AEROELASTIC LIMIT CYCLE OSCILLATIONS IN FIGHTER AIRCRAFT
British Library Conference Proceedings | 2006
|