Limited Wingspan Flapping Action Wing Of The Euler Equation Numerical Simulation

In this thesis, finite volume method and dual-time stepping method are employed to solve the 3-D unsteady Euler equations. The unsteady flow field around a finite-span flapping wing is simulated. The lift and thrust of the flapping wing for different cases are calculated. The factors which effect on the aerodynamic characteristics of flapping wing are analyzed.The main aspects of this dissertation are as follows:1. Employing the moving grid technique, a 3-D moving grid based on the transfinite interpolation is developed. This grid has better adaptation than the deforming grid for flapping wing.2. The 3-D unsteady Euler equations are derived. And the computational program based on these equations is developed to adapt for the calculations of flapping wing.3. The effects of every flapping control parameters on the aerodynamic characteristics of flapping wing are investigated. Its results lay a foundation for the further investigations of flapping wing micro air vehicles.As the computational results are in good agreement with reference data, the method given in this dissertation is correct and reliable. Applying this dissertation, the aerodynamic characteristics of flapping wing can be calculated, the effects of every factor can be analyzed and some qualitative instructions can be given.