文中以某型大长细比火箭弹为研究背景,利用基于N-S方程的CFD软件研究了海拔高度从0km到80km,马赫数从0.6~5.0时主要气动参数的变化情况。结果表明:海拔高度在30km以下时,升力系数、阻力系数和压心系数等随着海拔高度增加变化量较小;而到了30km以上高空时,随着海拔高度的增加,阻力系数和升力系数增加很多,压心前移明显,并且马赫数越小变化越剧烈。依据所得气动参数设计的高空飞行弹道与野外飞行试验结果相符,进一步验证了研究结果的可信度。

In this article, based on a rocket with high fineness ratio, its aerodynamic data was obtained with numerical simulation technology based N-S equations, and the aerodynamic characteristic in large range of altitude and Mach number from 0.6 to 5.0 was investigated. The research shows that when altitude is below 30 km, aerodynamic coefficients take a little change as altitude increases; But when it is above 30 km, and up to 50km and 80km, drag coefficient and lift coefficient increase greatly and pressure center moves ahead markedly, especially change greater when Mach number is lower. The designed ballistic trajectory based on the computational data accords with outfield flight test's results, which furthermore validates the computational method's reliability.