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本文从理论上对尾翼式脱壳穿甲弹的气动力特性进行了分析计算,并与[1]所给出的风洞试验结果进行了比较,其目的是分析理论计算方法的可靠性和计算误差范围。在计算中引用了[1]、[3]、[5]、[6]的有关理论和实验研究成果。计算结果表明,阻力系数、升力系数及其斜率、压力中心系数和前体阻力系数、俯仰力矩系数及其斜率的理论计算值与风洞试验值之间的相对误差分别在3％和5％以内。
In this paper, the aerodynamic characteristics of the tail-shell APF are theoretically calculated and compared with the results of the wind tunnel test given in [1]. The purpose of this paper is to analyze the reliability and calculation error range of the theoretical calculation method . The calculation of the reference [1], [3], [5], [6] on the theoretical and experimental research results. The calculated results show that the relative errors between the calculated values of drag coefficient, lift coefficient, slope, pressure center coefficient, precursor drag coefficient, pitch moment coefficient and slope are within 3% and 5%, respectively .