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本文介绍了一种应用有限基本解气动模型来计算尾翼下洗的方法。探讨了前翼后缘尾涡运动方向,以及尾翼方位角对下洗的影响。针对×-×型号的导弹得出了,当尾涡沿α/2方向运动时,下洗计算与试验值最为接近,以及下反能提高尾翼效率的结论。与其它计算方法相比,本文的突出优点在于:它不但能计及压缩性效应,而且能较精确地反映各部件的实际外形。
This article presents a method for calculating the fin washdown using a finite basic solution aerodynamic model. The moving direction of trailing vortex of front wing and the influence of tail angle on rinsing were discussed. For missiles of type × - ×, the conclusion is drawn that when the wake vortex moves in the α / 2 direction, the calculation of the laundering is the closest to the experimental value and the efficiency of the tail reversal improves the efficiency of the tail. Compared with other calculation methods, this article has the outstanding merit that it can not only consider the compressibility effect, but also reflect the actual shape of each component more accurately.