Numerische Simulation des Flatterverhaltens eines nichtlinearen 2D-Fluegel-Ruder-Systems in subsonischer Stroemung

The limited applicability of classical analysis methods to predict the flutter stability of nonlinear aeroelastic systems hinders the development and design process of modern airplanes. In this paper a time marching procedure is presented which, based on the coupling of the governing equations for the fluid and the structure applying different modelling concepts and discretizations (domain decomposition approach), enables the numerical simulation of the flutter behavior of a 2D wing/control-surface system with concentrated structural nonlinearities. Numerical experiments using the classical linear subsonic wing theory and an unsteady CFD Euler code demonstrate the practicability of the method and provide a deeper insight into the mechanisms of the 2D wing/control-surface flutter problem with special regard to nonlinear control-mounting stiffnesses. (orig.)Available from TIB Hannover: RN 437(99-23) / FIZ - Fachinformationszzentrum Karlsruhe / TIB - Technische InformationsbibliothekSIGLEDEGerman