摘要
本文介绍了风洞中进行模型气动阻尼特性试验的同时,获取飞行器气动静稳定性数据的基本原理。根据动态试验的频率数据,计算了五种再入外形的俯仰力矩系数的攻角导数,并与五座风洞中得到的大量静态试验数据做了比较。表明由动态法获得的静稳定性数据是可信的;并且易于观察粘性对稳定性的影响;在零攻角(或配平角)附近,动态法比静态法显示出更多的合理性。
This paper presents the results of the static stability of 5reentry Vehicles as Fig.2 by dynamic test technique in two supersonicwind tunnels and in three hypersonic wind tunnels.This results are compared with that obtained by conventional staticaerodynamic tests.It shows that the static stability data obtained fromdynamic test are in agreement with that obtained from static tests.
关键词
飞行器
气动力
稳定性
雷诺数效应
test technique
aerodynamic stability
Reynolds number effect
