摘要
在ＦＤ－０８风洞中，为了解采用侧壁支撑机构进行大攻角实验的可能性，进行了头部长细比３．５尖拱柱模型的亚音速实验，最大攻角达８０°。本文通过与Ａｍｅｓ１２英尺风洞实验结果的比较，介绍了实验结果并对实验结果作了初步讨论。
In order to have a knowledge about the possibility of doing high angle experiments in FD-08 wind tunnel with special support structure, we use a tangent ogive-cylinder model with a fineness ratio of 3.5to carry out the test in which angles of attack as high as 80° having compared with that of ames 12 feet wind tunnel. The author introducesthe result and gives a brief analysis.
关键词
气动力特性
亚音速
弹身
大攻角
风洞试验
aerodynamic characteristics
subsonic
bodies
highangle of attack
side forces
