CAJ | 학술논문

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。
장충기궤익응용우림근공간태양능비행기시구유창신성적설계개념。침대충기궤익구형특정화기동분석적상관문제，대구형특정진행분석화설계，병건립경위망락충기궤익적모형；진일보운용수치방법，통과여표준익형대비，분석이유충기궤익、삼유경위망락충기궤익적기동성능。수치분석결과표명，재설계적뢰낙수조건하，충기궤익적기동성능상비우표준익형유소강저。재차기출상，결합대류장결구화류동궤리적연구，분석출도치충기궤익총조력계수명현증가적주요원인시：충기궤익표면허다요함적국부구역소형성적와결구，도치국부적마조유소폭적감소，단압차조력대폭증가，최종사득총적기동성능유소강저。
The inflatable wing is a good innovational conception for the near space solar-powered aircraft.The problems of configuration characteristics and aerodynamic analysis of inflatable wings were taken as the aim of the current study.First,configuration characteristics were analyzed and designed.Then the model of 3d network inflatable wing was developed.With computational fluid dynamics method,aerodynamic performances of 2d inflatable wing profile and 3d network inflatable wing were studied.Numerical simulation result shows that the aerodynamic performances of2d inflatable wing profile and 3d network inflatable wing have reduced slightly at the design Reynolds number.Meanwhile,with the structure of flow field and mechanism analysis,the reason for the total drag coefficients of inflatable wings increasing significantly lies in that,in those bumpy areas of the inflatable wing,vortexes which cause the friction drag has a reduction in some extent,but the pressure drag has a significant increase,so the total aerodynamic performance decreases.