Department of Aerospace Engineering, Amirkabir University of Technology, 424 Hafez Avenue, Tehran, Iran
The main aim of this paper is to develop an efficient aeroelastic tool for predicting the flutter speed of a typical section in transonic regime. An implicit mesh-less method based on the Euler and Navier-Stokes equations are conducted to simulate the transonic fluid flow around an airfoil. This technique is applied directly to the differential form of the aerodynamic governing equations and the time integration is carried out using a dual-time implicit time discretization scheme. The capabilities of the flow solution method are demonstrated by flow computations around NACA0012 airfoil at different flow conditions. For structural dynamics simulation, a typical section model with pitching and plunging motion capability is considered. Finally, the aeroelastic analysis of the 2D model is performed by the consecutive simulation of both structural and aerodynamic domains. Also, the effect of viscosity and time interval choice between two structural and aerodynamic solvers on the flutter instability is studied. The comparison between the obtained results and those available in the literature shows the good accuracy of the present method.