摘要
为了研究高超声速飞行器尖化前缘热环境特点,对尖化前缘外形进行测热测压风洞试验,同时利用数值分析和理论手段开展尖化前缘热环境预示方法研究。获得了两种小尺寸前缘半径尖化前缘外形压力和热流的分布规律,分析了在半径较小的情况下,经典的Fay-Riddell驻点热流计算公式和前缘后掠圆柱方法的适用性。研究结果表明,Fay-Riddell公式在小尺寸的情况下已不再适用,采用层流后掠圆柱方法可以模拟尖化前缘中心线上的热环境。
The wind tunnel experiment is done to obtain the property of hypersonic vehicle with small radius sharp leading edge.The numerical simulation and the method in theory are also developed to study the heating environment prediction.The pressure and heating distribution on the hypersonic vehicle with two leading edge radii are obtained and the applicability of classical Fay-Riddell stagnation heating formula and the swept cylinder method for leading edge is studied in the case of small radius.The classical Fay-Riddell stagnation heating formula is not applicable to the small radius and the swept cylinder method for leading edge can be used for the heat on the centerline of the sharp leading edge.
作者
高莹莹
杨凯威
孔维萱
景昭
杨驰
Gao Ying-ying;Yang Kai-wei;Kong Wei-xuan;Jing Zhao;Yang Chi(Beijing Institute of Space Long March Vehicle,Beijing,100076)
出处
《导弹与航天运载技术》
CSCD
北大核心
2019年第6期112-116,共5页
Missiles and Space Vehicles
关键词
高超声速
尖化前缘
测热测压试验
热环境预示
hypersonic
sharp leading edge
wind tunnel experiment
heating environment prediction
