Aerodynamic Computation Of 3-D Unsteady Euler Equations For Wings With Control Surface

The finite-volume resolution scheme for the three dimensional steady and unsteady Euler equations is studied in this thesis. The algebraic method is used to generate C type 2D and C-H type 3D steady structured meshes. The rapid deforming techniques are developed to generate unsteady moving meshes. In order to increase the computation efficiency, artificial dissipation, variable time step and enthalpy damping acceleration techniques are used in the five-step Runge-Kutta time stepping. For the requirement of instantaneity, an implicit real-time discretisation is used, and the equations are integrated in a fictitiously pseudo time. This approach allows the real-time step to have two-order accuracy and accelerates the speed of convergence. Based on the theory of Mr. John K. Dukowicz and the algorithm of Mr. John D. Ramshaw, we have developed an algorithm of the so-called 'interpolating operator' for interpolation across the discontinuous surface of the control surface. The results of three dimensional steady and unsteady flows show that the methods developed in the thesis are effective.