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将充气机翼应用于临近空间太阳能飞行器是具有创新性的设计概念。针对充气机翼构形特征和气动分析的相关问题,对构形特征进行分析和设计,并建立经纬网络充气机翼的模型;进一步运用数值方法,通过与标准翼型对比,分析二维充气机翼、三维经纬网络充气机翼的气动性能。数值分析结果表明,在设计的雷诺数条件下,充气机翼的气动性能相比于标准翼型有所降低。在此基础上,结合对流场结构和流动机理的研究,分析出导致充气机翼总阻力系数明显增加的主要原因是:充气机翼表面许多凹陷的局部区域所形成的涡结构,导致局部的摩阻有小幅的减小,但压差阻力大幅增加,最终使得总的气动性能有所降低。
Applying inflatable wings to adjacent spaces Solar vehicles are innovative design concepts. According to the related problems of the configuration characteristics and the aerodynamic analysis of the inflatable wing, the configuration features are analyzed and designed, and the model of the inflatable wing of the latitude and longitude network is established. By using the numerical method and comparing with the standard airfoil, the 2D inflator Aerodynamic performance of airfoil with three-dimensional warp and weft wings. The numerical results show that the aerodynamic performance of the inflatable wing is lower than that of the standard airfoil at the designed Reynolds number. On this basis, the main reason for the obvious increase of the total drag coefficient of the inflatable wing is analyzed based on the study of the structure and flow mechanism of the flow field. The vortex structure formed by many recessed local areas of the inflating airfoil results in the local There was a slight decrease in friction resistance, but a significant increase in pressure drop resistance eventually resulting in a decrease in overall aerodynamic performance.