导弹气动特性工程计算通用程序设计与研究

Design and Study on the General Program of Missile Aerodynamic Characteristics Engineering Calculation

以三级以下弹箭常见的气动外形为计算模型，编制了气动特性工程计算通用程序（ＡＤＭ系统），该软件适用于计算马赫数０～１０、飞行攻角０～３０°范围内多种火箭和导弹的气动参数。利用风洞实验数据详细检验了计算误差，除跨音速段外，升力、阻力系数计算误差分别小于３％和３．５％，压心系数误差小于１％。经过防雹火箭和探空火箭使用验证，该程序用于火箭设计是可靠的。

The general program of aerodynamic characteristics engineering calculation (ADM system) is compiled by using the common aerodynamic configuration of the rocket or missile with less than three stages as a calculation model, it is suitable for calculating aerodynamic parameters of different types of rocket and missile which flight at 0～10 Ma with an attack angle of 0～30°. The calculated results are checked by the wind tunnel experiment. It is obtained that the calculated errors of the lift coefficient and the drag coefficient are less than 3%, 3.5% respecttively, and the pressure center coefficient error is less than 1% except for the transonic region. The program is verified to be reliable to rocket design through tests of antihail rocket and sounding rocket.