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.