Computation of aerodynamic damping in aeroelastic system based on analytical and numerical approach

0459369 - ÚT 2017 RIV CZ eng C - Konferenční příspěvek (zahraniční konf.)
Chládek, Štěpán - Horáček, Jaromír - Zolotarev, Igor
Computation of aerodynamic damping in aeroelastic system based on analytical and numerical approach.
ENGINEERING MECHANICS 2016. Praha: Ústav termomechaniky AV ČR, v. v. i., 2016 - (Zolotarev, I.; Radolf, V.), s. 238-241. ISBN 978-80-87012-59-8. ISSN 1805-8248.
[Engineering Mechanics 2016 /22./. Svratka (CZ), 09.05.2016-12.05.2016]
Grant CEP: GA ČR GA13-10527S
Institucionální podpora: RVO:61388998
Klíčová slova: aeroelastic instability, * aerodynamic damping and eigenfrequency analysis * fluid structure
Kód oboru RIV: BI - Akustika a kmity

The paper describes computation of aerodynamic damping and natural frequencies of aeroelastic systems. The damping is a critical parameter for the stability analysis of aeroelastic systems. Structural damping of the system is important for very low fluid flow velocities, however by increasing the flow velocity, the aerodynamic damping dominates in the instability search. The damping can be evaluated in time or in frequency domain. The presented computation of aerodynamic damping consists of two analytical and one numerical approach. The analytical approaches are represented by the well-known pk method and the unsteady panel method. The pk method is based on Theodorsen unsteady aerodynamics and on the computation of complex eigenvalues of the system as functions of the flow velocity. The unsteady panel method enables the computation of the interaction between aeroelastic system and fluid flow. The aerodynamic damping is evaluated in time domain from the system response to given initial conditions. The numerical approach is based on the finite volume method (FVM) modelling the complete fluid-structure interaction (FSI) coupled problem. The aerodynamic damping is also computed from the system response to a given initial condition. The results of the mentioned methods are compared for the profile NACA 0012 with two degrees of freedom (2-DOF) for plunge and pitch motion around an elastic axis.
Trvalý link: http://hdl.handle.net/11104/0260728