Euler Equation For Solving The Static Aeroelastic Problems

The research of this dissertation is focused on how to simulate numerically the steady flows around wing and aircraft by computational fluid dynamic method. On this base, the static aeroelastics problems of wing and aircraft are investigated by coupled with structure dynamic equation.On the base of generating three-dimensional unstructured grid by advancing-front method, an effective and well robust unstructured grid method is regenerated to solve the deformation of unstructured grid. So, a good foundation is created to solve the problem of the steady aerodynamic and aeroelastics.In this paper, 3-D Euler equations are solved using full implicit dual-time temporal derivatives and the cell-centred finite volume spatial discretization and four-stage Runge-kutta time- stepping scheme on unstructured mesh with standard convergence acceleration techniques such as local time stepping and implicit residual smoothing. Based on the above work, flow fields around wing and aircraft configuration have been achieved.In the thesis, flow fields around wing and aircraft are solved by Euler equations, then couple with structure dynamics equations to compute the elastatics deformation of wing and aircraft, the computation course are step by step when the structure elastatics is balance, finally we obtain the elastatics deformation and real form of wing and aircraft. 3-D M6-wing and super-critical airfoil wing and aircraft are used as examples to investigate their problem of the static aerodynamics elastatics. The results of flow fields and elastatics deformation are in good agreement with the experiments and document, which showed that the numerical solution method is correct and robust, we also obtain some significant conclusion from it.