摘要
在低速风洞中进行导弹大攻角试验时经常遇到大攻角下导弹轴向力为负的现象,这与高速试验时轴向力为正的现象存在本质差别,对其原因也众说纷纭,因此文中针对低速大攻角下导弹轴向力为负的原因开展研究。采用风洞测压试验的方法对大攻角下导弹头部截面压力分布特性进行了分析,得出了低速条件下导弹头部大面积负压所产生的吸力是导致导弹大攻角负轴向力的主要原因,并对低速范围雷诺数对导弹轴向力的影响进行了分析。
The axial force of missile is often negative at high angle of attack during low speed wind tunnel test. The phenomenon is quite different from positive axial force phenomenon during high speed wind tunnel test. The reasons of previous phenomenon have been argued. The reasons will be studied in the paper. The pressure distribution characteristics of missile nose section were studied by pressure measure- ment test at high angle of attack. The primary reason about negative axial force of missile at high angle of attack and low speed is due to the suction caused by large area negative pressure of missile nose. The effects of Reynolds number on axial force of missile were also studied.
出处
《弹箭与制导学报》
CSCD
北大核心
2013年第6期114-116,共3页
Journal of Projectiles,Rockets,Missiles and Guidance
关键词
导弹
低速
大攻角
轴向力
missile
low speed
high angle-of-attack
axial force
