摘要
本文分析了在任意滚动角下,极小展弦比翼身组合体的绕流模型,揭示了原有的气动力计算方法的缺陷,即,只考虑翼片之间的附着流干扰;提出新的翼片之间的干扰模型,除了考虑附着流干扰外,更要考虑侧缘分离涡对翼片的干扰,并引进涡干扰因子,于是,基于不可压的绕流理论,应用非线性面元法,计算该因子,与实验比较表明,本文方法不仅适用于小迎角的亚、跨、超音速流动,也适用于中等迎角的流动。
In this paper, a flow modal was considered for wing-body combination with very low aspect ratio at any rolling angle, and the wrong for traditional aerodynamic predicting method to be used to very low aspect ratio wing. Which just considers the attached flow interference in wings, was researched. A new in- terference model is offered, which considers not only the attached flow, but also the separated vortex shed from side edge of wings, and the vortex interference factor is introduced. Then the factor is computed using the nonlinear panel method based on the incompressible flow. The comparison of the theory with experiment shows that the method adapted not only subsonic, transonic and supersonic flow at small angle attack, but also at middle angle attack.
出处
《空气动力学学报》
CSCD
北大核心
2013年第1期99-102,共4页
Acta Aerodynamica Sinica
关键词
分离涡
细长翼
极小展弦比翼身组合体
任意滚动角气动力计算方法
separated flow
slender wing
wing-body combination with very low aspect ratio
predictingmethod for aerodynamic force at any rolling angle