Starting from a finite state model for a two-dimensional aerodynamic flow over an airfoil, the eigenmodes of the aerodynamic flow are determined. Using a small number of these aerodynamic eigenmodes, ie., a reduced-order model, the aeroelastic model is formed by coupling them to a typical section structural model with a trailing-edge flap. A free-play nonlinearity is modeled. Results are shown from the finite state model, the reduced-order model, and previous theoretical and experimental work. All results are in good agreement.
Reduced-Order Aerodynamic Model and Its Application to a Nonlinear Aeroelastic System
Journal of Aircraft ; 35 , 2
1998-03-01
Miscellaneous
No indication
English
Reduced-Order Aerodynamic Model and Its Application to a Nonlinear Aeroelastic System
Online Contents | 1998
|Aeroelastic Stability Analysis Using Reduced Order Aerodynamic Models
British Library Conference Proceedings | 1999
|