高超声速再入钝头体表面热流计算
Numerical study of aeroheating predictions for hypersonic reentry bodies
查看参考文献10篇
|
文摘
|
基于跟踪流线的轴对称比拟法,采用纯工程算法、Euler数值计算与边界层内工程算法相结合的方法,对高超声速再入钝头体的表面热流进行了计算,并将计算结果与风洞实验数据进行了对比,两者吻合较好,验证了两种工程算法在计算高超声速飞行器热环境方面的正确性.将两种工程算法与数值求解N-S方程进行对比,表明工程算法在迎风面的热流计算方面有较高的精度,节约了计算时间,很好地满足高超声速飞行器概念研究和设计的需要. |
|
其他语种文摘
|
In order to calculate the heating rates on hypersonic blunt bodies quickly and effectively, two engineering methods were developed based upon the axisymmetric analogue which required tracking the invis-cid surface streamlines. Engineering predictions in the boundary layer were used in both methods. However, method No. 1 used engineering predictions out of the boundary layer, and in method No. 2 the boundary-layer edge conditions were determined by the CFD method solved by Euler equations of three dimensions. Results of the two methods are in good agreement with the existing experimental data, which validates the correctness of the methods in calculating the heating rates on hypersonic vehicles. Results of these two engineering methods were also compared with those of CFD method solved by N-S equations, which indicates that the engineering methods save much calculating time and also have precision on predicting the heating rales on windward. |
|
来源
|
北京航空航天大学学报
,2006,32(12):1395-1398 【核心库】
|
|
关键词
|
热流
;
高超声速
;
数值计算
;
工程算法
|
|
地址
|
1.
北京航空航天大学,航空科学与工程学院, 北京, 100083
2.
中国科学院,力学研究所, 北京, 100080
|
|
语种
|
中文 |
|
文献类型
|
研究性论文 |
|
ISSN
|
1001-5965 |
|
学科
|
航空 |
|
文献收藏号
|
CSCD:2644703
|
参考文献 共
10
共1页
|
|
1.
Peter A G.
Computational fluid dynamics technology for hypersonic applications.AIAA-2003-2829,2003
|
CSCD被引
1
次
|
|
|
|
|
2.
Dietiker J F.
Challenges in the heat transfer computations of high speed flows,2004:2004
|
CSCD被引
1
次
|
|
|
|
|
3.
李君哲. 气动热CFD计算的格式效应研究.
北京航空航天大学学报,2003,29(11):1022-1025
|
CSCD被引
18
次
|
|
|
|
|
4.
王发民. 高超声速升力体气动力气动热数值计算.
空气动力学学报,2001,19(4):439-445
|
CSCD被引
12
次
|
|
|
|
|
5.
Kinney D J.
Aero-thermodynamics for conceptual design,2004:2004
|
CSCD被引
1
次
|
|
|
|
|
6.
Wurster K E. Flowfield and vehicle parameter influence on results of engineering aerothermal methods.
Journal of Spacecraft,1991,28(1):16-22
|
CSCD被引
1
次
|
|
|
|
|
7.
Hamilton H H. Approximate method for calculating heating rates on three-dimensional vehicles.
Journal of Spacecraft and Rockets,1994,31(3):345-354
|
CSCD被引
6
次
|
|
|
|
|
8.
Dejarnette F R. A method for calculating laminar and turbulent convective heat transfer over bodies at an angle of attack[R].
A method for calculating laminar and turbulent convective heat transfer over bodies at an angle of attack.NASA-CR-101678,1969
|
CSCD被引
1
次
|
|
|
|
|
9.
Miller C G. Experimental and predicted heating distributions for biconics at incidence in air at mach 10[R].
Experimental and predicted heating distributions for biconics at incidence in air at mach 10.NASA-TP-2334,1984
|
CSCD被引
2
次
|
|
|
|
|
10.
Cleary J W. Effects of angle of attack and bluntness on laminar heating rate distribution of a 15°cone at a mach number of 10.
Effects of angle of attack and bluntness on laminar heating rate distribution of a 15°cone at a mach number of 10.6.NASA-TND-5450,1969
|
CSCD被引
1
次
|
|
|
|
|
了解气象卫星更多信息，请访问