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国家自然科学基金(11202224)

作品数:4 被引量:8H指数:2
相关作者:陈皓范晶晶温玉芬陈星星马友林更多>>
相关机构:中国运载火箭技术研究院更多>>
发文基金:国家自然科学基金中国博士后科学基金更多>>
相关领域:理学航空宇航科学技术更多>>

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钝头体中的广义雷诺比拟关系
2020年
钝头体壁面的摩阻和热流分布规律不同,平板流动中的雷诺比拟关系在钝头体壁面失效.文章在前期高超声速广义雷诺比拟理论研究工作的基础上,利用数值仿真的方法对不同外形和来流参数条件下的钝头体广义雷诺比拟关系开展进一步研究.通过建立钝头体绕流边界层的理论分析模型,得到了钝头体壁面雷诺比拟系数的线性分布预示公式.采用数值求解N-S方程的方法,计算了圆柱和幂次体壁面的摩阻和热流以及二者之间的比拟系数.通过与前期数值和理论结果对比,以及计算收敛性和网格无关性检验,对数值方法进行了验证.通过在不同雷诺数(Re_∞=3.98×10~2~1.59×10~6)和马赫数(M_∞=3~12)条件下的计算结果对比分析雷诺比拟系数的分布,总结了钝头体中广义雷诺比拟关系受外形和来流条件的影响,评估了广义雷诺比拟理论的适用性.研究发现,在较高雷诺数条件下,离驻点较远的下游(θ> 60°)部位,雷诺比拟系数的分布不同程度地偏离理论预示的线性规律.相比于圆柱外形,幂次体壁面的雷诺比拟系数分布的线性规律相对较好,其分布斜率略低于圆柱壁面的结果.研究表明,如果针对实际外形和雷诺数进行适当修正,可以提高广义雷诺比拟关系的预示精度.
陈星星陈皓范晶晶温玉芬张正马友林
关键词:摩阻热流高超声速
高超声速稀薄流动中传热与剪切的非线性效应研究
结合直接模拟蒙特卡洛(DSMC)计算验证,先后研究了微钝前缘驻点区域的non-Fourier传热现象和尖前缘平板绕流中non-Newton剪切现象。首先在近连续流动领域,基于对Burnett方程热流和应力本构方程的分析,...
王智慧陈星星余永亮
关键词:高超声速非线性DSMC
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An analytical study on nonequilibrium dissociating gas flow behind a strong bow shockwave under rarefied conditions被引量:6
2013年
In this paper, an explicitly analytical shock mapping relation is approximately deduced based on the theoretical modeling of the chemical nonequilibrium stagnation flow towards a slightly blunted nose. Based on the relation, the complex reacting stagnation flow problem can be discussed under the framework of the simplest normal shockwave flow. Therefore, a quantita- tively meaningful criterion for dissociation nonequilibrium flow, that is a specific Damk hler number Da d , is naturally intro- duced as the ratio of the mapping length of the stagnation streamline and the characteristic nonequilibrium scale. Da d is found to be dependent on the flow's rarefaction criterion W r , that is a specific Knudsen number. Then, based on Da d , a normalized analytical formulation is obtained to quantitatively predict the actual degrees of dissociation at the outer edge of the stagnation point boundary layer (SPBL). At last, the direct simulation Monte Carlo (DSMC) method is employed to validate the analytical results, and the related flow mechanism is discussed. The present study not only shows nonequilibrium features of the flow problem, but also provides an indispensable basis for the following study on the nonequilibrium SPBL heat transfer.
WANG ZhiHuiBAO LinTONG BingGang
关键词:HYPERSONICDSMC
Modeling study of rarefied gas effects on hypersonic reacting stagnation flows
<正>Recent developing of the near space hypersonic sharp-leading vehicles has raised a necessity to fast and ac...
Zhihui WangLin Bao
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Theoretical modeling of chemical nonequilibrium stagnation point boundary layer heat transfer under rarefied conditions被引量:3
2013年
This paper theoretically studies the recombination-dominated nonequilibrium reacting flow inside the stagnation point bound- ary layer (SPBL) and the heat transfer characteristics under rarefied conditions. A general model is intuitively proposed to de- scribe the energy transfer and conversion along the stagnation streamline towards a slightly blunted nose with non-catalytic wall surface. It is found that the atoms recombination effects inside the SPBL could be equivalent to a modification on the de- gree of dissociation in the external flow. As a result, a recombination nonequilibrium criterion Dar, that is a specific DamktSh- let number, is introduced to characterize the nonequilibrium degree of the reacting flow in the SPBL, and then, based on the general model and Dar, a bridging function indicating the nonequilibrium chemical effects on the SPBL heat transfer is estab- lished. By using the explicitly analytical bridging function, the flow and heat transfer mechanisms, including the real gas flow similarity law and the nonequilibrium flow regimes classification, are discussed. In addition, the direct simulation Monte Carlo (DSMC) method has also been employed to systematically validate the analytical results.
WANG ZhiHuiBAO LinTONG BingGang
关键词:DSMC
Solid rocket motor propellant grain burnback simulation based on fast minimum distance function calculation and improved marching tetrahedron method被引量:2
2021年
To efficiently compute arbitrary propellant grain evolution of the burning surface with uniform and non-uniform burning rate for solid rocket motor,a unified framework of burning surface regression simulation has been developed based on minimum distance function.In order to speed up the computation of the mini-mum distance between grid nodes of grain and the triangular mesh of burning surface,a fast distance querying method based on the equal size cube voxel structure was employed.An improved marching tetrahedron method based on piecewise linear approximation was carried out on second-order tetrahedral elements,achieved high-efficiency and adequate accuracy of burning surface extraction simultaneously.The cases of star grain,finocyl grain,and non-uniform tube grain were studied to verify the proposed method.The observed result indicates that the grain burnback computation method could realize the accurate simulation on unstructured tetrahedral mesh with a desirable performance on computational time.
Pengfei RENHongbo WANGGuofeng ZHOUJiani LIQiang CAIJiaquan YUYa YUAN
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