Abstract
In this paper the flutter behavior of a typical wing is investigated. The study is performed by presented Deferential Quadrature Method (DQM). The aerodynamic part adopted Wagner functions to model subsonic regime. Quasi steady and unsteady aerodynamics are considered to estimate the instability speed of the structure. Based on the presented model, a code is developed, for an arbitrary typical section beam. The obtained results validated the existing methods in the literature. The proposed method provides the advantage of finding the modes of oscillation and other dynamic parameters with less than 0.2% difference.
Highlights
The flutter behavior of coupled two- and three-dimensional systems have been investigated both numerically and analytically in a vast amount of research
Each of the aerodynamic theories has been presented in both time and frequency domains
Later, perusing unsteady aerodynamics modeling was developed by such new techniques as Finite state induced flow models and reduced order model (ROM)
Summary
The flutter behavior of coupled two- and three-dimensional systems have been investigated both numerically and analytically in a vast amount of research. Introduced this theory to describe the lift response of structures in unsteady flows In this area, some semianalytical schemes have been suggested to determine instability condition. The K method (Bisplinghoff, Ashley, & Halfman, 2013; Hodges & Pierce, 2011) is another approach to studying structural response in an unsteady flow This method introduces artificial structural damping to the system and determines only the instability point. The instability condition of the typical airfoil and Goland wings in subsonic flow using differential quadrature method are investigated. In this method, an appropriate Wagner function is utilized as the aerodynamic theory. The presented model will be compared with those of other investigations in the frequency domain
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