Numerical study of aeroheating predictions for hypersonic reentry bodies
-
摘要: 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.Abstract: 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 inviscid 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 rates on windward.
-
Key words:
- heating rate /
- hypersonic /
- numerical simulation /
- engineering code
-
[1] Peter A G. Computational fluid dynamics technology for hypersonic applications . AIAA-2003-2829, 2003 [2] Dietiker J F, Hoffmann K A. Challenges in the heat transfer computations of high speed flows . AIAA-2004-0993, 2004 [3] 李君哲, 阎超. 气动热CFD计算的格式效应研究[J]. 北京航空航天大学学报, 2003, 29(11):1022-1025 Li Junzhe, Yan Chao. Research on scheme effect of computational fluid dynamics in aerothermodynamics[J]. Journal of Beijing University of Aeronautics and Astronautics, 2003, 29(11):1022-1025(in Chinese) [4] 王发民, 沈月阳, 姚文秀. 高超声速升力体气动力气动热数值计算[J]. 空气动力学学报, 2001, 19(4):439-445 Wang Famin,Shen Yueyang,Yao Wenxiu. Aerodynamic and aerothermal numerical simulation of hypersonic lifting body configuration[J].ACTA Aerodynamica Sinica, 2001,19(4):439-445(in Chinese) [5] Kinney D J. Aero-thermodynamics for conceptual design . AIAA-2004-0041, 2004 [6] Wurster K E, Zoby E V, Thompson R A. Flowfield and vehicle parameter influence on results of engineering aerothermal methods[J]. Journal of Spacecraft,1991,28(1):16-22 [7] Hamilton H H, Franceis A G. Approximate method for calculating heating rates on three-dimensional vehicles[J]. Journal of Spacecraft and Rockets,1994,31(3):345-354 [8] Dejarnette F R, Tai T C. A method for calculating laminar and turbulent convective heat transfer over bodies at an angle of attack .NASA-CR-101678, 1969 [9] Miller C G. Experimental and predicted heating distributions for biconics at incidence in air at mach 10 . NASA-TP-2334, 1984 [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 10.6 . NASA-TND-5450, 1969 -
点击查看大图
计量
- 文章访问数: 2823
- HTML全文浏览量: 40
- PDF下载量: 1569
- 被引次数: 0
下载:
