IMECH-IR  > 力学所知识产出(1956-2008)
高超声速飞行器测热试验研究
Alternative TitleHeat flux measurement test of the hypersonic vehicle
刘嘉; 姚文秀; 李静美; 王发民
Source Publication流体力学实验与测量
2004-03-15
Volume18Issue:1Pages:29-32,37
Abstract在JF-8脉冲风洞中,来流马赫数Ma=8.0,来流单位长度雷诺数Re/L=1.47×107和2.52×107(1/m)两种试验条件下,对高超声速飞行器1/20缩尺模型进行了表面气动热的测量.模型攻角α=0°,10°,15°,20°,25°和30°.试验给出机身对称面、翼前缘、立尾前缘等处的热流率分布.机头部分最大热流率与由Fay-Riddell公式计算的驻点热流Q0率接近,翼前缘最大热流率在全机身中最大,约为Q0的2倍,因此翼前缘的热环境是最严酷的.
Keyword高超声速飞行器 热流率 风洞试验
Indexed ByCSCD
Language中文
CSCD IDCSCD:1500723
Citation statistics
Cited Times:2[CSCD]   [CSCD Record]
Document Type期刊论文
Identifierhttp://dspace.imech.ac.cn/handle/311007/41906
Collection力学所知识产出(1956-2008)
Corresponding Author刘嘉
Recommended Citation
GB/T 7714
刘嘉,姚文秀,李静美,等. 高超声速飞行器测热试验研究[J]. 流体力学实验与测量,2004,18(1):29-32,37.
APA 刘嘉,姚文秀,李静美,&王发民.(2004).高超声速飞行器测热试验研究.流体力学实验与测量,18(1),29-32,37.
MLA 刘嘉,et al."高超声速飞行器测热试验研究".流体力学实验与测量 18.1(2004):29-32,37.
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