阻尼导数只能用风洞或弹道试验来确定。
The damping derivatives can only be determined experimentally in the wind tunnel or ballistic range.
计算结果与风洞实验值比较表明，本方法精度较好，是进行尾翼弹气动力特性分析和外弹道设计的一个有力工具。
Comparisons between computations and wind tunnel experiments show that the accuracy of the code is ideal. It is useful for analyses of aerodynamic characteristics and exterior ballistic design.
该方法选用航空炸弹质点弹道模型，采用虚拟风洞数值模拟得到的炸弹阻力定律，结合实弹靶试数据，对弹道系数进行了符合计算。
In the method particle trajectory model of certain aviation bomb is chosen, drag law by the numerical simulation based on the virtual wind-tunnel is adopted.
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