任意截面弹体的翼身干扰系数估算方法研究

Method study on wing-body interference coefficient for missiles with arbitrary shape cross section

从小扰动线化速位方程出发,结合细长体理论,建立了任意截面弹体法向气动力与截面形状系数之间的相关性;采用二维鳞片法求解速位方程可以得到截面形状系数,从而进行单独弹体气动力估算。根据部件组拆法思想,对这一工程估算方法进行推广,提出一种适合于任意截面导弹翼身干扰系数的估算方法,该方法得到的预测结果和吹风实验、文献数据比较符合较好。采用以上方法对矩形截面的翼身组合体进行估算,具有较好的精度。

This paper, based on the small disturbance slender-body theory, has established the theory relation between the aerodynamic normal force of bodies with arbitrary shape cross-section and their geometrical functions. The disturbance velocity potential is got by calculating linear equation with the panel method, then the arbitrary cross section shape coefficients are numerically integrated. The method for predicting the wing-body interference coefficient for missiles with arbitrary shape cross section is established. The method can be used for both the arrangement of middle signal wing and other arrangements. Results predicted by this method are compared with experimental data and the accuracy of this method is found to be very good within the constraints of slender body theory.