半模机翼振动对气动性能影响的风洞试验研究

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

为了验证翼型振动测压试验结果和有关振动数值模拟文献的计算结果,设计完成了对称翼型NA-CA0012和层流翼型NACA64-210两种半模机翼的低速风洞振动试验。通过专门研制的半模振动模型,选取5种激振方式,用直接测力法得到了模型在静态和不同激振方式下升力特性变化曲线,分别研究了振动频率、雷诺数、自然转捩和固定转捩、数据采集方式等参数对机翼气动特性的影响。试验结果表明:半模机翼振动的气动特性与二元翼型和数值计算情况有所不同,其影响因不同翼型构型、不同采集方式和翼面不同流动模式等会产生不同效果。并对产生原因进行初步探讨。

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.