This paper describes the airliner wing flutter sensitivity analysis. The sensitivity coefficients define the influence of the structural parameter changes to tthe structure eigenvalue and flutter stability characteristics. Evaluated structural parameters represent the possible changes of the structure due to the installation of the smart high-lift devices at the leading and trailing edge region. In general, we can suppose the increasing of the mass and mass moment of inertia around the elastic axis and decreasing of the stiffness. Described effects are ordinarily considered destabilizing regarding the flutter. The main aim of the presented work is to evaluate the impact of components to the stability and to define the most critical regions or parameters. and Obsahuje seznam literatury
Assessment of ultimate aeroelastic response of slender facades equipped with thin plexiglass sheets. The wave approach is used for modeling of aeroelastic wind forcing. The analysis of structural response is based on the transient dynamics. Some theoretical approaches are specified with experimental verification in the wind canal. The comparison of numerical and experimental approaches is made in order to demonstrate the efficiency of the procedures suggested. and Obsahuje seznam literatury
The subject of the paper is the numerical simulation of the interaction of two-dimensional incompressible viscous flow and a vibrating airfoil inserted in a channel (e.g. wind tunnel). A solid airfoil with two degrees of freedom can rotate around the elastic axis and oscillate in the vertical direction. The numerical simulation consists of the finite element soluton of the Navier-Stokes equations coupled with the system of ordinary differential equations describing the airfoil motion. The time dependent computational domain and a moving grid are taken into account with the aid of the Arbitrary Lagrangian-Eulerian (ALE) formulation of the Navier-Stokes equations. High Reynolds numbers up to 106 require the application of a suitable stabilization of the finite element discretization. Numerical results are compared with an experiment. and Obsahuje seznam literatury
In this paper the numerical approximation of a two dimensional aeroelastic problem is addressed, where nonlinear effects are considered. For the flow model we use the Navier-Stokes equations, spatially discretized by the FE method and stabilized with a modification of the Galerkin Least Squares (GLS) method. The motion of the computational domain is treated with the aid of the Arbitraty Lagrangian Eulerian (ALE) method. The structure model is considered as a solid body with two degrees of freedom (bending and torsion). The motion is described with the aid of a system of nonlinear differential equations and coupled with the flow model by the strongly coupled algorithm. and Obsahuje seznam literatury