Propeller Slipstream The Numerical Simulation Of The Wing / Machine Interference

This thesis concentrates on the application of CFD techniques to simulate the effect of turbo-propeller slipstream on the parts behind the propeller. Combining the momentum theory of the propeller with the CFD method, actuator disk model is introduced in N-S and Euler solution to predict the effects of turbo-propeller slipstream on a clean wing, high-lift systems and a whole aircraft.There are two ways which combine the actuator disk model with the finite volume method studied in this thesis. The first way is adding the actuator disk inside a single grid block. The other way is adding the model as a special boundary at the interface of two grid block. Both of them simulate the slipstream of a single propeller successfully. Simulate the effect of turbo-propeller slipstream on a clean wing, high-lift systems and an aircraft by the later method and compare these results with the case which is without the slipstream. Chimera grid, one-to-one block and patched-grid techniques are used to generate the grids of these three cases.The results show that, the aerodynamic characteristics of an aircraft with a propeller have good accuracy with the experiment results. The slipstream of propeller could increase the parts' lift behind the propeller. The increase of lift which is provided from the flap is evidence. The lift is increased as the thrust coefficient increases. The comparison between the numerical results and the experimental indicates that the methods which this thesis introduced are suitable for the study of the influence of slipstream to the parts behind it.