Missile Datcom 软件的全称为Missile Data Compendium，是由美国空军飞行力学实验室开发的一款气动力工程计算软件。弹道计算时需要获得弹体在不同马赫数、海拔、速度...条件下飞行时的气动力系数。一般可以使用 数值算法 和 工程算法 两种方式，（1）数值算法 利用 Fluent、CFD++ 等软件进行一系列复杂的前处理、求解器设置及后处理才可以进行计算，缺点显而易见，既考验使用者 Fluent、CFD++ 等软件的使用能力，又对电脑cpu等硬件的性能设置了门槛，普通的台式和笔记本难以堪当此任。（2）工程算法 是利用经验数据、实验数据及数学公式对弹体的气动力系数进行求解，Missile Datcom 软件就是应用了此种方式，优点：对使用者极其友好，通过看使用说明手册即可快速上手进行求解计算，并且计算速度快、对电脑配置没有要求，普通的笔记本、台式就可以。

一、Missile Datcom 的种类

Missile Datcom 拥有很多版本，如1997版、2011版，接下来介绍三款都是2011版。主要分为 Missile Datcom 无界面版 （我最喜欢的一个版本）、Missile Datcom 有界面版 1号 、Missile Datcom 有界面版 2号 。

二、Missile Datcom 无界面版

打开后就是下面的三个文件，即：在这里插入图片描述上图中的for005.dat文件就是输入文件，里面包含 $FLTCON（弹体飞行条件参数）、$ REFQ（弹体结构参数）、 $AXIBOD （弹体轮廓参数）、$ FINSET（舵、弹翼、尾翼等结构参数）。

DERIV RAD
DIM M
$FLTCON
 NALPHA = 11.0,
 ALPHA = -5.0,-4.0,-3.0,-2.0,-1.0,0.0,1.0,2.0,3.0,4.0,5.0,6.0,
 NMACH = 4.0,
 MACH = 0.650,0.800,0.930,1.500,
 ALT = 0.00,0.00,0.00,0.00,
$END
$REFQ
 SREF = 0.011310,
 LREF = 0.120000,
 XCG = 0.422900,
 RHR = 400.000000,
$END
$AXIBOD
 NX = 31.0,
 X = 0.00000000,0.00382000,0.00938000,0.01400000,0.01846000,
     0.02434000,0.03189000,0.04020000,0.04587000,0.05175000,
     0.05454000,0.06392000,0.07687000,0.08947000,0.10753000,
     0.15606000,0.18021000,0.20110000,0.22328000,0.25164000,
     0.28746000,0.31408000,0.34530000,0.37658000,0.40578000,
     0.43903000,0.46965000,0.50304000,0.53643000,0.60281000,
     0.70490000,
 R = 0.00359000,0.00636000,0.00918000,0.01121000,
     0.01323000,0.01524000,0.01599000,0.01682000,0.01870000,
     0.02063000,0.02156000,0.02156000,0.02763000,0.03276000,
     0.03899000,0.05079000,0.05493000,0.05781000,0.05936000,
     0.05969000,0.05781000,0.05493000,0.05025000,0.04459000,
     0.03898000,0.03276000,0.02574000,0.02155000,0.01737000,
     0.01737000,0.01737000,
$FINSET1
 SECTYP = HEX,
 NPANEL = 8.,
 PHIF = 0.00,45.00,90.00,135.00,180.00,225.00,270.00,315.00,
 XLE = 0.640,
 SWEEP = 13.4,13.4,60.0,60.0,
 SSPAN = 0.017,0.030,0.036,0.049,
         0.054,
 CHORD = 0.065,0.067,0.065,0.044,
         0.026,
 STA = 0.0,0.0,0.0,0.0,
       0.0,
 ZUPPER = 0.003000,0.003000,0.003000,0.003000,
          0.003000,
 LFLATU = 0.065000,0.067000,0.065000,0.044000,
          0.026000,
$END
*SAVE
DAMP
SPIN
BUILD
PART
PLOT
PRESSURES
*SOSE
PRINT VORTEX
NEXT CASE

当 for005.dat 文件完成后，即可进行计算，出现cmd命令框之后输入1，然后回车。如下图：

在这里插入图片描述计算完成后文件夹中出现许多文件，汇总的气动力系数结果文件为 for042.csv 中，使用者可对照使用手册将所需的气动力系数挑选出来。此外，如果想要查看 for005.dat 中建立好的模型，可使用 Tecplot 360 EX 软件（网上有破解版）打开 for022.dat 文件即可看到模型的三维效果图。