摘要
文章介绍了在8m×6m低速风洞中对某冲压式翼型伞进行的试验研究。文中给出了有关的技术方法,并对典型的试验结果进行了讨论。这一国内首创的风洞试验技术,可为翼型伞设计提供利用其他试验手段难以得到的翼伞操稳特性气动参数。
In this paper, wind tunnel test research on aerodynamic performance of a type of parafoil is introduced.Test techniques concerned and some typical consequent are presented here.Using this domestic new test technique in wind tunnel, we can acquire the aerodynamic control and stability parameters , which can not be gained by other ways.
出处
《航天返回与遥感》
1999年第4期1-4,共4页
Spacecraft Recovery & Remote Sensing
