亚、超音速小侧滑角机翼升力面理论和数值计算方法

本文推导出侧缘与自由流不平行的常值面涡半无限角翼基本解,其特征是从面涡小块背风侧缘拖出的涡不是顺着自由流,而是沿着侧缘拖出,从而克服了用Woodward方法计算侧滑翼绕流中使用对称分划小块的困难,提出了适用于从亚音速直到超音速范围的推广的Woodward方法。本方法将问题分解为若干个对称与反对称问题,大大地节省了计算机内存量或计算时间。本文还从基本方程,或者直接从数值计算方法出发,推导出准相似律。计算结果与精确解以及和其他方法的结果符合得很好。

LIFTING SURFACE THEORY AND THE NUMERICAL METHOD OF WINGS WITH SMALL ANGLES OF SIDESLIP AT SUBSONIC AND SUPERSONIC SPEEDS

In this paper we have derived the fundamental solutions of the flow over semi-infinite angular wings with constant load, of which the side-edge is not parallel to the free stream. The feature of the solutions is that the vortices issued from the leeward side-edge go along this edge rather than in the direction of the free stream. With the help of these solutions, we can overcome the difficulties Dillenius and Nielson have experienced in using symmetrical subdivisions to construct the finite elements for sideslipping wings, and extend Woodward method, so that it is applicable to wings with small angles of sideslip for subsonic and supersonic speeds. The problem is divided into symmetrical and asymmetrical parts, thus allowing a great saving of computer storage and operation time. Besides, a quasi-similar rule is derived from the governing equation or directly from the numerical method. The results obtained are in good agreement with those obtained by the exact theory and other methods.