Aeroelastic stability analysis is carried out with a structural cubic nonlinearity in torsional stiffness, for a two-degree-of-freedom airfoil. This analysis was carried out using a state space formulation for the aerodynamic model. This formulation enables hard coupling between the aerodynamics and the structural dynamics. The stability of the system is determined by carrying out an eigenvalue analysis. This analysis was applied to the case of a NACA 64A006 airfoil at a freestream Mach number of 0.85. As limit cycle oscillations can occur piror to the flutter point for nonlinear spring stiffness, a time response analysis is carried out in order to determine system behaviour. The set of conditions considered in this study produced lower flutter speeds with a nonlinearity than the linear flutter speed.
Aeroelastic stability analysis of an airfoil with structural nonlinearities using a state space unsteady aerodynamics model
Aeroelastische Stabilitätsanalyse eines Tragflügelprofils mit konstruktiven Nichtlinearitäten unter Verwendung der Zustandsraumformulierung für ein instationäres aerodynamisches Modell
1995
11 Seiten, 7 Bilder, 25 Quellen
Conference paper
English
British Library Conference Proceedings | 1995
|Aeroelastic Analysis of an Airfoil Using Eigenmode Based Reduced Order Unsteady Aerodynamics
British Library Conference Proceedings | 1995
|