高雷诺数二维充气机翼构形的气动特性

针对基于二维充气机翼的构形特征进行高雷诺数条件下的气动特性分析.首先通过对二维充气机翼构形特征的设计，建立了描述逼近程度的误差参数和若干模型；进一步运用数值方法，通过与标准翼型的对比，分析充气机翼的气动性能及其误差参数的敏感性.数值结果表明:在高雷诺数条件下，充气机翼的气动性能相对于标准翼型有所降低.同时，结合对流场特征的分析，从机理上解释二维充气机翼与标准翼型气动性能差异形成的原因，即导致总的阻力系数明显增加的主要原因是其凹凸起伏的表面对充气机翼表面压力分布所引起的变化，局部压力升高从而大幅增加了压差阻力. 

Aerodynamic performance of configurations of two-dimension inflatable wings under high Reynolds number

The aerodynamic performance analysis based on the configurations of two-dimension inflatable wings under high Reynolds number was analyzed. Firstly, configuration characteristic of the two-dimension inflatable wing was designed to define an offset parameter describing the degree of approximation between an inflatable wing profile and a standard airfoil, then several models were developed. Furthermore, with the numerical method, aerodynamic performance of the inflatable wing and the sensibility of the offset parameter was studied and compared with the standard airfoil. Numerical result showed that the aerodynamic performance of the inflatable wing had loss to a certain degree under high Reynolds number. Meanwhile, with the flow field characteristic analysis, the reason for the total drag increasing significantly was explained from mechanism that, in those bumpy areas, the pressure distribution changed a lot, so the increase of the local pressure caused significant increase of pressure drag.