旋转鸭式导弹洗流气动力干扰分析与计算

研究了旋转鸭式导弹前翼涡迹的扭曲变化,提出了计算洗流气动力干扰的数值方法。根据实验观测和分析,建立了计算扭曲涡迹的数学模型。由于导弹绕纵轴旋转,涡强和起始位置均随时间变化。计算旋涡洗流对后体和尾翼的气动力干扰效应有两种方法:一种采用细长体理论,适合于小展弦比尾翼;另一种采用反流定理,适合于中等展弦比尾翼。计算表明:前翼旋涡洗流除降低尾翼升力外,在旋转导弹上还要产生侧向力、偏航力矩和滚动力矩。这种现象可归入攻角和旋转的耦合气动力效应成为马格努斯效应的一个组成部分。

Analysis and Calculation of the Wash Field and Its Effects on the Aerodynamic Characteristics of a Rolling Canard Missile

A study is made of the wakes shed from the wing panel of a rolling canard controlled missile and a numerical method with a computer program for calculating the wakes and their interference effects on the rolling configuration is developed . A twisted vortex line model is established based on physical analysis and is found in conformity with the experiment . The strength of vortices and their positions that change with time are determined by numerical analysis. Two methods are given for calculating the interference effects of the wash field on the afterbody and the combined section of the body and the tail. One of the methods is based on the slenderbody theory which is for the low aspect ratio tail while the other is based on the reciprocal theorem and it is for the moderate aspect ratio tail. Analysis and calculation show that , in addition to the loss of the tail lift which occurs in nonrolling cases,a side force, yawing moment and rolling moment would can also be produced by the wakes . This fact can be directly ascribed to the interaction or coupling between angle of attack and rolling , and it is included in the Magnus effects.