Experimental Investigation Methods on Low Reynolds Number Plane Cascade

The conventional airfoil design system is based on high Reynolds number,but the development of UAV(unmanned aerial vehicle) has offered the new demands on airfoil design and experimental verification under low Reynolds number condition.This paper analyses the theory and methods for low Reynolds number cascade aerodynamic performance.The reconstructive project and experiment adjusting methods of facility are given,and low Reynolds number flow field after the reconstruction based on test data is analyzed.In China,it is the first time that aerodynamic performance parameters change under low Reynolds number of a high subsonic speed diffused airfoil are got by means of test.