Experiment investigation for vibration on aerodynamics of a half model wing in wind tunnel

In order to validate the experimental results accomplished with two-dimensional airfoil model and computational results from references, the vibration test of half-model wing respectively with NACA0012 aerofoil and NACA64-210 aerofoil is conducted in NF-3 wind tunnel. Through the specially designed elastic model with an exciting source which has an electric engine and five eccentric pieces on the top of wing, the aerodynamic characteristics are investigated and analyzed by directly measuring force using a box balance. The effecting factors, such as frequency, Reynolds number, boundary layer transition and data acquisition mode, are analysed in the paper. It is shown that the lift aerodynamic characteristic of the half-model is different with that of airfoil model and numerical computation. It is affected by the aerofoil contour, the modes of data acquisition and boundary layer transition, etc. The analysis of causes needs further study in the future.