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本文介绍亚、跨音速导弹纵向气动力特性计算的有限差分方法。采用园柱座标系,用变步长的混合差分格式进行线超松弛改进迭代计算。速势方程考虑了x向大扰动,并把精确边界条件嵌入到头部的速势方程中,以适用于计算钝头外形的要求。对尾部收缩的弹体,翼涡沿其平面伸展到收缩部分,以模拟涡面对尾翼和尾段的影响。 所建立的程序适用于计算任意形状旋成体弹身,翼身组合体及翼身尾组合体的表面压力分布和纵向气动力系数。 为鉴定方法的有效性和程序的正确性,对三个不同的气动外形进行了计算,与风洞实验结果比较,基本符合。
This paper introduces the finite difference method for calculating the longitudinal aerodynamic characteristics of submarine and transonic missiles. The cylindrical coordinate system was used to improve the iterative calculation of line over relaxation by using the mixed step difference variable format. The velocity equation takes into account the large perturbations in the x direction and embeds the precise boundary conditions in the head velocity equations to fit the requirements for the blunt tip shape. For the constricted projectile, the vortex extends along its plane to the constricted part to simulate the effect of the vortex on the tail and the tail. The established procedure applies to the calculation of the surface pressure distribution and longitudinal aerodynamic coefficient of spin-body, wing-body and wing-tail assemblies of arbitrary shape. In order to verify the effectiveness of the method and the correctness of the procedure, three different aerodynamic shapes were calculated and compared with the wind tunnel experiment results, basically in line with.