摘要
运用结构化网格求解三维Euler方程,计算得到边界层外缘无粘流场气流参数;利用无粘流场气流参数和表面流函数的方法计算了飞行器无粘表面流线分布;在理论和半经验公式的基础上,计算了定比热比和变比热比情况下驻点热流密度,非驻点区域采用参考焓、局部相似性等方法来确定飞行器表面的气动加热,实现了数值算法与工程算法的耦合.上述方法用于求解高超声速钝双锥的表面热流分布,计算结果与经典的热流公式和实验结果进行对比,平均精度为10%左右,满足高超声速飞行器概念研究和初步设计的需要.
The boundary layer edge conditions were determined by 3-D CFD（Computational fluid dynamics） method and solved by 3-D Euler equation on structured grids; the wall stream trace was computed based on the stream function theory and flow parameters; the heating rates of staypoint with constant and variable specific heats were computed by the theory and semi-experienced formulas, while the heating predictions of non-staypoint were calculated based on the reference enthalpy theory and locally similar theory. The calculated results of the heating rates of double blunt biconic are in good agreement with existing experimental data and classic engineering methods, with average precision about 10%. It is applicable to the parametric design of hypersonic aircrafts.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2009年第1期65-69,共5页
Journal of Aerospace Power
关键词
表面热流
高超声速
工程算法
流线
heating rate
hypersonic
engineering prediction
stream trace
