摘要
在 FD-09低速风洞中进行了零侧滑大攻角下尖拱圆柱形弹体侧力的实验研究。试验是在雷诺数从2.3×10~5至9.2×10~5范围内进行的。攻角从-4°到70°。试验结果表明:侧力的“起始角”当长细比增大时减小,当头部顶角增大时增大。侧力的方向和量值对雷诺数和滚转角的反应是敏感的。头部边条有助于消除侧力。
An experimental investigation was conducted in theFD-09 Low speed wind tunnel to determine the side forces on ogive-cylinder bodies of missiles at zero sideslip & high angles of attack.Tests were conducted over a Reynolds number range from 2.3×10~5 to9.2×10~5.The angle of attack varied from—4~0 to 70~0.The results show that the angle of attack of onset of side forcedecreases as fineness ratio increases,and increases as nose vertex angleincreases.The direction and magnitude of the side force are sensi-tive to the Reynolds number and roll angle.The nose strakes tend toeliminate the side force.
关键词
气动力
测量
旋成体
旋涡
aerodynamic measurement
body of revolution
vortex
