高超声速稀薄过渡流气动热关联计算方法研究
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摘要
本文对高超声速稀薄过渡流气动热的关联参数和计算方法进入行了研究。对驻点区和飞行器表面不同的流动区域给出了流态划分准则。在理论分析的基础上，对通常广泛采用的稀薄气动热数据关联参数—Cheng’s参数进行了改进。通过耦合压力系数，建立了一组能应用于有攻角情况下高超声速飞行器表面稀薄气动热数据分析的关联参数，根据对现有的大量国内外低密度风洞实验数据的数据关联，用最小二乘法进行数据拟合，建立了计算有攻角情况下飞行器表面稀薄气动热的关联计算方法。为了计算任意三维外型飞行器表面的稀薄气动热，本文采用了无粘表面流线轴对称比拟法与稀薄气动热的关联计算方法相结合，建立了计算有攻角情况下飞行器表面稀薄气动热的工程计算方法。通过计算结果与实验结果的比较表明，计算的沿迎风母线、背风母线及沿周向的热流分布均与实验数据符合较好。
A correlation method of heat transfer rate in hypersonic rarefied flow was present in this paper. Flow criterion was introduced for stagnation point region and the body of the vehicle. On the basis of therotical analysis, the raefied heat transfer rate correlation parameter-Cheng's parameter was modified. A set of correlation parameters, which could be used to analysis rarefied flow heating to hypersonic vehicles with attack angle, has been established through coupling with pressure coefficient. According to correlating many Low-dencity wind tunnels experimental dates at home and abroad, the least squares procedure adopted to fit the data, a engineering method of rarefied heat transfer rates on the surface of vehicle with attack angle has been established. In order to calcalate rarefied heat transfer on the surface of arbitrariness configuration, combined the inviscid surface streamlines and axisymmtric annalog, the engineer calculational method of rarefied heat transfer on the surface of vehicle with attack angle was been established. Calculational results showed heat transfer rates (along upwind and leeside generatrix, circumferential direction) were well agreement with the experimental data.
A correlation method of heat transfer rate in hypersonic rarefied flow was present in this paper. Flow criterion was introduced for stagnation point region and the body of the vehicle. On the basis of therotical analysis, the raefied heat transfer rate correlation parameter-Cheng's parameter was modified. A set of correlation parameters, which could be used to analysis rarefied flow heating to hypersonic vehicles with attack angle, has been established through coupling with pressure coefficient. According to correlating many Low-dencity wind tunnels experimental dates at home and abroad, the least squares procedure adopted to fit the data, a engineering method of rarefied heat transfer rates on the surface of vehicle with attack angle has been established. In order to calcalate rarefied heat transfer on the surface of arbitrariness configuration, combined the inviscid surface streamlines and axisymmtric annalog, the engineer calculational method of rarefied heat transfer on the surface of vehicle with attack angle was been established. Calculational results showed heat transfer rates (along upwind and leeside generatrix, circumferential direction) were well agreement with the experimental data.
引文
[1] 杨炳尉，徐居福．飞行器气动加热和防热计算手册，《科技简报》编辑组，1979．
[2] Cheng, H.K. The Blunt Body Problem in Hypersonic Flow at Low reynolds Number, IAS-63-92,Jan., 1963.
[3] Coleman, G. T., Metcatf, S. C. and Berry, C.J. Heat Transfer To Hemisphere Cylinders and Bluff Cylinders Betweell Continuum and Free Molecular Ftow Limits. R.G.D 10th pp393～404.
[4] Boylam, D.E. Laminar Heat Transfer on Sharp and Blunt Ten-Degree cones in Conical and parallet Low-Density Flow, August 1973 AEDC-TR-73-106.
[5] J.N. Moss, and G. A. Bird, Drect Sinlutation of Transition Flow for Hypersonic Reentry conditions. AIAA--84--0223
[6] J.L. Shinn, nd A. L- Simmonds, "Comparison of Viscous-Shock Layer Heating Analysis with Shuttle Flight Data in Slip Flow Regime". AIAA-84-0226.
[7] 彭治雨：返回舱稀薄气动热计算，气动中心超高速研究所，1994，XH940042．
[8] Engel C.D., MINIVER UPGRADE FOR THE AVID SYSTEM, VoLume I, NASA CR 172212.
[9] 彭治雨：高超声速稀薄过渡流绕钝锥的气动热计算，气动中心超高速研究所，1990，TR-5-90063．
[10] 谢砚儒，DF-22与JL-1在FD-17风洞中的实验数据关联方法，气动中心超高速研究所，1985，5BG85-412。
[11] 张金涛：低密度风洞气动加热实验研究，气动中心超高速研究所，1990．CARDC-TR-5．90064
[12] 华威，DF-5真假目标在稀薄气体中气动加热实验研究，气动中心超高速研究所，1981，5BG81-48。
[13] Varren M.Rohsenow, Handbook of heat transfer fundamentals. Second Edition, 1985. New York.
[14] G. A. Bird, "Low Density Aerotheramdyaseics. " AIAA 20th Thermophysics Conference, iune 1985, AIAA85--0994
[15] V.K.Dogra, R.G. Wilmoth and J.N. Moss, Aerothermodynamics of a 1.6 m
Diameter sphere in hypersonic rarefied flow. AIAA91-0773 Jan., 1991.
[16] 李明，徐中华。在低密度流中用红外热图技术测量模型表明气动加热。《流动显示99》第214-219页，中国空气动力学会，中国力学学会，1999。
[17] XIE YANRU and HUA WEI, "1Some Calculative Formulae of Rarefied Aerodyaseic Characteristics on Simple Bodies" Proceedings of the 14th international Symposium on R.G. D, Juty 19849.
[18] G. A. Bird, "Molecular Gas Dynanics." 1976.
[19] DeJarnette F.R., Calculation of Inviscid Surface Streamlines and Heat Tranfer on Shuttle Type Configurations, NASA CR-111921.
[20] 谢砚儒，梁杰等，计算远程弹头稀薄气动力特性的当地化方法研究，气动中心超高速研究所，1990，EJ-5-990015。
[2] Cheng, H.K. The Blunt Body Problem in Hypersonic Flow at Low reynolds Number, IAS-63-92,Jan., 1963.
[3] Coleman, G. T., Metcatf, S. C. and Berry, C.J. Heat Transfer To Hemisphere Cylinders and Bluff Cylinders Betweell Continuum and Free Molecular Ftow Limits. R.G.D 10th pp393～404.
[4] Boylam, D.E. Laminar Heat Transfer on Sharp and Blunt Ten-Degree cones in Conical and parallet Low-Density Flow, August 1973 AEDC-TR-73-106.
[5] J.N. Moss, and G. A. Bird, Drect Sinlutation of Transition Flow for Hypersonic Reentry conditions. AIAA--84--0223
[6] J.L. Shinn, nd A. L- Simmonds, "Comparison of Viscous-Shock Layer Heating Analysis with Shuttle Flight Data in Slip Flow Regime". AIAA-84-0226.
[7] 彭治雨：返回舱稀薄气动热计算，气动中心超高速研究所，1994，XH940042．
[8] Engel C.D., MINIVER UPGRADE FOR THE AVID SYSTEM, VoLume I, NASA CR 172212.
[9] 彭治雨：高超声速稀薄过渡流绕钝锥的气动热计算，气动中心超高速研究所，1990，TR-5-90063．
[10] 谢砚儒，DF-22与JL-1在FD-17风洞中的实验数据关联方法，气动中心超高速研究所，1985，5BG85-412。
[11] 张金涛：低密度风洞气动加热实验研究，气动中心超高速研究所，1990．CARDC-TR-5．90064
[12] 华威，DF-5真假目标在稀薄气体中气动加热实验研究，气动中心超高速研究所，1981，5BG81-48。
[13] Varren M.Rohsenow, Handbook of heat transfer fundamentals. Second Edition, 1985. New York.
[14] G. A. Bird, "Low Density Aerotheramdyaseics. " AIAA 20th Thermophysics Conference, iune 1985, AIAA85--0994
[15] V.K.Dogra, R.G. Wilmoth and J.N. Moss, Aerothermodynamics of a 1.6 m
Diameter sphere in hypersonic rarefied flow. AIAA91-0773 Jan., 1991.
[16] 李明，徐中华。在低密度流中用红外热图技术测量模型表明气动加热。《流动显示99》第214-219页，中国空气动力学会，中国力学学会，1999。
[17] XIE YANRU and HUA WEI, "1Some Calculative Formulae of Rarefied Aerodyaseic Characteristics on Simple Bodies" Proceedings of the 14th international Symposium on R.G. D, Juty 19849.
[18] G. A. Bird, "Molecular Gas Dynanics." 1976.
[19] DeJarnette F.R., Calculation of Inviscid Surface Streamlines and Heat Tranfer on Shuttle Type Configurations, NASA CR-111921.
[20] 谢砚儒，梁杰等，计算远程弹头稀薄气动力特性的当地化方法研究，气动中心超高速研究所，1990，EJ-5-990015。