Understanding and Development of a Prediction Method of Transonic Limit Cycle Oscillation Characteristics of Fighter Aircraft
Understanding and Development of a Prediction Method of Transonic Limit Cycle Oscillation Characteristics of Fighter Aircraft
- New search for: J. J. Meijer
- New search for: A. M. Cunningham
- New search for: J. J. Meijer
- New search for: 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 semiempirical LCO prediction method is being developed. Its preliminary version was applied to several configurations and correctly identified those which have encountered LCO. It has already shown the potential for application early in the design process of new aircraft to determine and understand the nonlinear aeroelastic characteristics. An upgraded form is described and results of the latest predictions are used to further assess various parametric effects. The ultimate refinements are expected from unsteady wind tunnel force and pressure measurements for which preliminary results are presented.
Document information
Understanding and Development of a Prediction Method of Transonic Limit Cycle Oscillation Characteristics of Fighter Aircraft
1992
17 pages
Report
No indication
English
Aircraft , Aerodynamics , Aeroelasticity , Flutter analysis , Harmonic oscillation , Transonic flutter , Wing oscillations , Fighter aircraft , Prediction analysis techniques , Unsteady aerodynamics , Vibration mode , Equations of motion , Pressure distribution , Separated flow , Time lag , Time marching , Trailing edges , Transonic flow , Foreign technology
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