Study On The Effects Of The Aerodynamic Performance Of The Airfoil Caused By Rotating Cylinder And Trailing Edge Flap

At present,wind turbine is the main device to convert into electricity and to make effective use of wind energy.And its performance affects the utilization of wind energy directly.In order to make the wind turbine operate efficiently and reduce the maintenance cost in manufacturing and operation,designing reasonable and efficient blades becomes the key step in the design process of wind power equipment.Researchers are committed to finding efficient control techniques to improve the overall performance of wind turbines.The use of the leading edge rotating method for flow control has many characteristics such as facilities simple operation and low cost.The trailing edge flap is easy to use in wind turbine for its small structure.And it has good performance of high frequency and fast response.Research has shown that the blade load decreases obviously after applying the trailing edge flap control,especially the fatigue load.This paper researched the aerodynamic performance of the blade after combining the leading edge rotation and the trailing edge flap in the same wind turbine blade,using the method of computational fluid dynamics(CFD).This paper verified the effectiveness of the selected computational model in a two-dimensional S809 airfoil developed by the US renewable energy laboratory.The cylindrical dimensions of the S809 airfoil with leading edge rotation were preliminarily designed.The effects of rotating cylinder speed on the aerodynamic performance of the two-dimensional S809 airfoil were studied after the rotation control was applied.It is found that the aerodynamic performance of a two-dimensional S809 airfoil with a leading edge rotation control is greatly improved at large angles of attack,but the change is not obvious at small angles of attack.This paper studied the effect of trailing edge flap deflection angle and the deflection position changes on blade aerodynamic performance with the leading edge of the rotating cylinder speed settled.It is found that the lift characteristics of the combination of S809 airfoil was improved at small angle of attack by deflecting the trailing edge flap,while it was not significantly improved only with the leading edge control of two-dimensional S809 airfoil.