热化学非平衡流及其辐射现象的实验和数值计算研究
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摘要
本文工作主要涉及高超声速热化学非平衡流及其辐射特性的实验和数值计算研究。
实验研究工作为：1)、使用中国空气动力研究与发展中心(CARDC)再入物理弹道靶设备和脉冲曝光时间5ns的Nd-YAG激光器，进行了高超声速钢球模型激波脱体距离的测量实验。在国内第一次得到了非平衡流无烧蚀激波流场清晰的有限条纹激光干涉照片和阴影照片，测量得到高精度的头部激波脱体距离。测量误差约为5％，模型飞行速度5.0～5.5km／s，靶压10～80mmHg。使用了CFD及CFI技术辅助设计和确定实验方案。2)、测量了多个状态的高超声速球模型非平衡流场的可见光辐射强度，并对实验技术和方法进行分析研究。测量采用双狭缝式可见光辐射计，中心波长位于绿光波段(517.8nm、519.8nm)，半宽度为6.6nm。球模型飞行速度为4.8～5.7km／s，靶压10～80mmHg。
数值研究工作包括了热化学非平衡流场及其辐射特性的计算。其中，热化学非平衡流数值模拟工作为：
1)、对热化学非平衡流的物理化学模型进行分析，选择Park双温度模型、Gupta空气11组元化学反应模型及相应的输运模型、振动离解耦合模型、能量交换模型耦合Navier-Stokes方程组求解流动问题。2)、对NND格式、Roe格式、AUSM类格式以及相应的数值计算技术(包括加速收敛技术、MUSCL插值方法、熵修正技术、源项对角隐式处理等)在轴对称、三维热化学非平衡流数值模拟中的应用进行了比较和分析。结果表明，AUSM类格式性能最优，LUSGS隐式处理方法计算效率较高。提出了一种新的熵修正方法，与网格无关并可减少对边界层解的影响。3)、编制完成包含上述物理化学模型及数值技术的热化学非平衡流计算程序TCNEQ(2D、3D)。程序具有良好的结构网格适应性及模块化程度，气动力及热流计算结果与文献吻合，通过了算例考核及实验验证。4)、在国内第一次进行了球模型激波脱体距离实验和计算的高精度对比研究，并使用CFI技术进行了全流场的实验验证。采用多种气体模型计算实验状态的球模型激波脱体距离，并采用CFI技术处理为阴影图和有限干涉条纹图，直接与实验照片对比进行流场验证。5)、采用TCNEQ3D程序对Apollo飞船返回舱大攻角全流场(含底部及近尾流区域)进行数值模拟；计算了返回舱气动力系数，并与文献及实验结果进行对比；分析表明，非平衡现象可能是造成返回舱飞行实验数据与风洞实验数据不一致的原因之一。
国防科学技术大学研究生院学位论文
热化学非平衡流辐射特性的数值计算工作有如下部分:
1、根据热空气辐射的三种类型，综合了量子力学、原子分子物理学以及光
谱学的相关知识，分别对空气组元的连续谱辐射、原子线辐射和分子带辐射机
制进行了详细的分析和讨论，给出了热化学非平衡态下求解辐射发射系数和吸
收系数(含诱导辐射)、的相关公式。以本文实验状态为算例条件，在求得热化
学非平衡流场数值解的基础上，采用“逐线计算”的精细辐射模型，在波长
ZOOOA~S0000A的范围内对原子、分子跃迁各机制详细计算辐射的谱发射系数
和谱吸收系数。
2、发展了精细光谱辐射模型的计算与应用分析技术，编制了适用于弹道靶
高温气体辐射研究的“辐射计测量数值模拟程序”，在国内第一次应用于弹道
靶光辐射实验的分析研究。通过构造规则的“辐射计算网格”，进行三维空间
的数据重构，并数值积分求解辐射输运方程(Radiative Transfer Equation)，实现
了弹道靶模型光辐射测量过程的数值模拟。计算可以得到流场光辐射信号在模
型穿越辐射计视场范围时的完整时间历程，从而实现了可见光辐射实验测量与
数值计算的高精度对比。计算并分析了半阴影区和壁面温度对测量结果的影响
程度，模型可见光辐射数值计算结果与实验测量数据基本一致。
综合上述研究工作，分别完成了热化学非平衡流场数值模拟程序
TcNEQ(2D、3D)、高温空气光谱辐射特性计算程序、高超声速模型流场光辐射
信号计算程序，三个部分形成了一套完整的、功能齐全的高温气体动力学计算
分析软件系统。其中，TCNEQ系列程序可以选择采用各种数值计算技术，应用
于不同热化学模型、复杂外形飞行器的全流场数值模拟和气动力、气动热计算
与分析;高温空气光谱辐射特性计算程序和三维流场光辐射信号计算程序可以
对飞行器本体及绕流场的光辐射特性进行计算与分析。该软件系统在飞行器外
形设计、目标识别与跟踪、通讯、突防、流场特性研究等方面都可发挥作用。
流场光辐射信号计算程序经过改进，也可以应用于其他实验设备(如激波管)
的高温气体辐射特性研究，对相关实验方法的设计、实验结果的分析整理及型
号工程应用有重要的实用意义。
关键词:高超声速，热化学非平衡，辐射，数值模拟，弹道靶实验
第Xll页
This paper is mainly about experimental and numerical study of hypersonic thermochemical nonequilibrium flow and its radiation characteristics. Experimental research includes:l).Highly accurate shock wave standoff distance of the hypersonic spherical steel model has been obtained in China Aerodynamics Research and Development Center (CARDC). The main facilities used are the Reentry Physics Ballistic Range and a high performance, pulsed Nd-YAG laser with pulse duration of 5ns. It is the first time in China to have obtained the clear laser interferogram and shadow graphs of the thermochemical nonequilibrium flowfield around the model without ablation. The error of measurement is about 5%. The model's flight velocity is 5.0~5.5km/s, and the chamber's pressure is 10~80mmHg. Computational Fluid Dynamics (CFD) and Computational Flow Imaging (CFI) methods are used to design and determine the experiment's scheme.2).The radiant intensities of the nonequilibrium flowfield of the hypersonic spherical model in visible light have been obtained under several conditions, and the experimental techniques have been analyzed. A double-slit visible-light radiometer is used with the central wavelength located in the band of green light(517.8nm and 519.8nm) and the half-width 6.6nm. The model's flight velocity is 4.8~5.7km/s, and the chamber's pressure is 10~80mmHg.Numerical research includes the computation of thermochemical nonequilibrium flowfield and its radiation characteristics.The research on numerical simulation of thermochemical nonequilibrium flow includes:1). Analyzing the physical and chemical models for thermochemical nonequilibrium flow. The Park's two-temperature model, Gupta's reaction model with 11 air species and related transportation model, vibration-dissociation coupling model and energy exchange mechanisms are chosen to solve the Navier-Stokes equations.2).Comparing and analyzing the NND scheme, Roe scheme, AUSM-family scheme and related numerical techniques(including the technique for speeding up convergence, MUSCL method, entropy fix method, diagonal implicit processing of source terms, etc.) in simulating thermochemical nonequilibrium flow. The result indicates that the AUSM-family scheme is the best while the implicit LUSGS method has the highest computational efficiency. This paper also puts forward a new
entropy fix method, which is independent of the computational grid and is capable to minimize the dissipative effect in the boundary layer.3).The computational codes TCNEQ (2D, 3D), which are for axial symmetrical and three-dimensional flow, have been established by using the above-mentioned physical and chemical models. The codes have good adaptability with structured grids and high level of modularization. The computational aerodynamics and heat flux are consistent with those of the references and the codes have been validated using experimental data.4).It is the first time in China that high accurate comparative research between the experimental and computational shock wave standoff distances is carried out. Several air models are used in computation. The whole flowfield is experimentally validated using CFI method. With CFI method, the numerical results are processed to generate computational shadowgraphs and finite-fringe interferogram, which can be compared with the experimental photos directly.5).The three-dimensional code TCNEQ3D is used to simulate the whole flowfield around the reentry capsule of the Apollo spacecraft (including the base and wake flow). The aerodynamic coefficients of the capsule are calculated and compared with the references and experimental data. The analysis indicates that the nonequilibrium phenomenon is possibly one of the reasons for the discrepancy between the capsule's flight data and the wind tunnel data.The research on numerical computation of the radiation characteristics of thermochemical nonequilibrium flow includes:1. On the basis of the three types of the high temperature air radiation, analyzing and discussing in detail of the mechanism of continuum, atomic lines and m
实验研究工作为：1)、使用中国空气动力研究与发展中心(CARDC)再入物理弹道靶设备和脉冲曝光时间5ns的Nd-YAG激光器，进行了高超声速钢球模型激波脱体距离的测量实验。在国内第一次得到了非平衡流无烧蚀激波流场清晰的有限条纹激光干涉照片和阴影照片，测量得到高精度的头部激波脱体距离。测量误差约为5％，模型飞行速度5.0～5.5km／s，靶压10～80mmHg。使用了CFD及CFI技术辅助设计和确定实验方案。2)、测量了多个状态的高超声速球模型非平衡流场的可见光辐射强度，并对实验技术和方法进行分析研究。测量采用双狭缝式可见光辐射计，中心波长位于绿光波段(517.8nm、519.8nm)，半宽度为6.6nm。球模型飞行速度为4.8～5.7km／s，靶压10～80mmHg。
数值研究工作包括了热化学非平衡流场及其辐射特性的计算。其中，热化学非平衡流数值模拟工作为：
1)、对热化学非平衡流的物理化学模型进行分析，选择Park双温度模型、Gupta空气11组元化学反应模型及相应的输运模型、振动离解耦合模型、能量交换模型耦合Navier-Stokes方程组求解流动问题。2)、对NND格式、Roe格式、AUSM类格式以及相应的数值计算技术(包括加速收敛技术、MUSCL插值方法、熵修正技术、源项对角隐式处理等)在轴对称、三维热化学非平衡流数值模拟中的应用进行了比较和分析。结果表明，AUSM类格式性能最优，LUSGS隐式处理方法计算效率较高。提出了一种新的熵修正方法，与网格无关并可减少对边界层解的影响。3)、编制完成包含上述物理化学模型及数值技术的热化学非平衡流计算程序TCNEQ(2D、3D)。程序具有良好的结构网格适应性及模块化程度，气动力及热流计算结果与文献吻合，通过了算例考核及实验验证。4)、在国内第一次进行了球模型激波脱体距离实验和计算的高精度对比研究，并使用CFI技术进行了全流场的实验验证。采用多种气体模型计算实验状态的球模型激波脱体距离，并采用CFI技术处理为阴影图和有限干涉条纹图，直接与实验照片对比进行流场验证。5)、采用TCNEQ3D程序对Apollo飞船返回舱大攻角全流场(含底部及近尾流区域)进行数值模拟；计算了返回舱气动力系数，并与文献及实验结果进行对比；分析表明，非平衡现象可能是造成返回舱飞行实验数据与风洞实验数据不一致的原因之一。
国防科学技术大学研究生院学位论文
热化学非平衡流辐射特性的数值计算工作有如下部分:
1、根据热空气辐射的三种类型，综合了量子力学、原子分子物理学以及光
谱学的相关知识，分别对空气组元的连续谱辐射、原子线辐射和分子带辐射机
制进行了详细的分析和讨论，给出了热化学非平衡态下求解辐射发射系数和吸
收系数(含诱导辐射)、的相关公式。以本文实验状态为算例条件，在求得热化
学非平衡流场数值解的基础上，采用“逐线计算”的精细辐射模型，在波长
ZOOOA~S0000A的范围内对原子、分子跃迁各机制详细计算辐射的谱发射系数
和谱吸收系数。
2、发展了精细光谱辐射模型的计算与应用分析技术，编制了适用于弹道靶
高温气体辐射研究的“辐射计测量数值模拟程序”，在国内第一次应用于弹道
靶光辐射实验的分析研究。通过构造规则的“辐射计算网格”，进行三维空间
的数据重构，并数值积分求解辐射输运方程(Radiative Transfer Equation)，实现
了弹道靶模型光辐射测量过程的数值模拟。计算可以得到流场光辐射信号在模
型穿越辐射计视场范围时的完整时间历程，从而实现了可见光辐射实验测量与
数值计算的高精度对比。计算并分析了半阴影区和壁面温度对测量结果的影响
程度，模型可见光辐射数值计算结果与实验测量数据基本一致。
综合上述研究工作，分别完成了热化学非平衡流场数值模拟程序
TcNEQ(2D、3D)、高温空气光谱辐射特性计算程序、高超声速模型流场光辐射
信号计算程序，三个部分形成了一套完整的、功能齐全的高温气体动力学计算
分析软件系统。其中，TCNEQ系列程序可以选择采用各种数值计算技术，应用
于不同热化学模型、复杂外形飞行器的全流场数值模拟和气动力、气动热计算
与分析;高温空气光谱辐射特性计算程序和三维流场光辐射信号计算程序可以
对飞行器本体及绕流场的光辐射特性进行计算与分析。该软件系统在飞行器外
形设计、目标识别与跟踪、通讯、突防、流场特性研究等方面都可发挥作用。
流场光辐射信号计算程序经过改进，也可以应用于其他实验设备(如激波管)
的高温气体辐射特性研究，对相关实验方法的设计、实验结果的分析整理及型
号工程应用有重要的实用意义。
关键词:高超声速，热化学非平衡，辐射，数值模拟，弹道靶实验
第Xll页
This paper is mainly about experimental and numerical study of hypersonic thermochemical nonequilibrium flow and its radiation characteristics. Experimental research includes:l).Highly accurate shock wave standoff distance of the hypersonic spherical steel model has been obtained in China Aerodynamics Research and Development Center (CARDC). The main facilities used are the Reentry Physics Ballistic Range and a high performance, pulsed Nd-YAG laser with pulse duration of 5ns. It is the first time in China to have obtained the clear laser interferogram and shadow graphs of the thermochemical nonequilibrium flowfield around the model without ablation. The error of measurement is about 5%. The model's flight velocity is 5.0~5.5km/s, and the chamber's pressure is 10~80mmHg. Computational Fluid Dynamics (CFD) and Computational Flow Imaging (CFI) methods are used to design and determine the experiment's scheme.2).The radiant intensities of the nonequilibrium flowfield of the hypersonic spherical model in visible light have been obtained under several conditions, and the experimental techniques have been analyzed. A double-slit visible-light radiometer is used with the central wavelength located in the band of green light(517.8nm and 519.8nm) and the half-width 6.6nm. The model's flight velocity is 4.8~5.7km/s, and the chamber's pressure is 10~80mmHg.Numerical research includes the computation of thermochemical nonequilibrium flowfield and its radiation characteristics.The research on numerical simulation of thermochemical nonequilibrium flow includes:1). Analyzing the physical and chemical models for thermochemical nonequilibrium flow. The Park's two-temperature model, Gupta's reaction model with 11 air species and related transportation model, vibration-dissociation coupling model and energy exchange mechanisms are chosen to solve the Navier-Stokes equations.2).Comparing and analyzing the NND scheme, Roe scheme, AUSM-family scheme and related numerical techniques(including the technique for speeding up convergence, MUSCL method, entropy fix method, diagonal implicit processing of source terms, etc.) in simulating thermochemical nonequilibrium flow. The result indicates that the AUSM-family scheme is the best while the implicit LUSGS method has the highest computational efficiency. This paper also puts forward a new
entropy fix method, which is independent of the computational grid and is capable to minimize the dissipative effect in the boundary layer.3).The computational codes TCNEQ (2D, 3D), which are for axial symmetrical and three-dimensional flow, have been established by using the above-mentioned physical and chemical models. The codes have good adaptability with structured grids and high level of modularization. The computational aerodynamics and heat flux are consistent with those of the references and the codes have been validated using experimental data.4).It is the first time in China that high accurate comparative research between the experimental and computational shock wave standoff distances is carried out. Several air models are used in computation. The whole flowfield is experimentally validated using CFI method. With CFI method, the numerical results are processed to generate computational shadowgraphs and finite-fringe interferogram, which can be compared with the experimental photos directly.5).The three-dimensional code TCNEQ3D is used to simulate the whole flowfield around the reentry capsule of the Apollo spacecraft (including the base and wake flow). The aerodynamic coefficients of the capsule are calculated and compared with the references and experimental data. The analysis indicates that the nonequilibrium phenomenon is possibly one of the reasons for the discrepancy between the capsule's flight data and the wind tunnel data.The research on numerical computation of the radiation characteristics of thermochemical nonequilibrium flow includes:1. On the basis of the three types of the high temperature air radiation, analyzing and discussing in detail of the mechanism of continuum, atomic lines and m
引文
[1]. J. D. Anderson, Hypersonic and High-temperature Aerodynamics. McGraw-Hill Book Company, 1989:11～24
[2]. Devendra S. Parmar, Qamar A. Shams. Aerothermal Instrumentation Loads to Implement Aeroassist Technology in Future Robotic and Human Missions to MARS and Other Locations Within the Solar System. NASA/TM-2002-211459. April 2002.
[3]． 黄志澄．高超声速飞行器空气动力学．北京：国防工业出版社，1995
[4]. R. A. Mercier, M. F. Ronald. Hypersonic Technology (HyTech) Program Overview. AIAA 98-1566, 1998
[5]. C. Rothmund, D. Scherrer Propulsion System for Airbreathing Launcher in the French PREPHA Program. AIAA 96-4498, 1996
[6]. M. Bouchez Scramjet Combustor Design in French PREPHA Program-Status in 1996. AIAA 96-4582, 1996
[7]. M. Bouchez, X. Montazel. Hydrocarbon-Fueled Airbreathing Propulsion for High Speed Missiles. AIAA 98-3729, 1998
[8]. W. W. Koschel. Basic Hypersonic Propulsion Research in German University. AIAA 98-1634, 1998
[9]. M. Kallenberg, E. Von Lavante. The Dynamics of Unsteady Supersonic Combustion. AIAA 98-3319, 1998
[10]. M. Maita, H. Kubota., Y. Moriguchi. Japanese Spaceplane/RLV Programme. IAF 97-V.4.05,1997
[11]. A. R. Srikrishan, J. Kurian, V. Sriramulu. A Comparative Experimental Study of Supersonic Combustion. ISABE 99-7055, 1999
[12]. F. Nasuti, M. Onofri. Numerical Analysis of the Slipstream Effect in Extemal Expansion Nozzle. ISABE 99-7122, 1999
[13]. R. N. Gupta, J. M. Yos, R. A. Thompson. A review of Reaction Rates and Thermodynamic and Transport Properties for an 11-species Air Model for Chemical and Thermal Non-equilibrium Calculations to 30000K. NASA RP 1232, 1990
[14]． 徐根兴主编．导弹与航天丛书(防空导弹系列)：目标和环境的光学特性．北京：宇航出版社，1995
[15]． 王福恒，王嵩薇．近代科学技术中的原子分子辐射理论．成都：成都科技大学出版社，1990：17，22，25，42
[16]．吴颖川．计算光学流动显示技术的研究与应用．中国空气动力研究与发展中心博士学位论文．2003年6月
[17]. Chul Park. Stagnation-Point Radiation for Apollo 4-A Review and Current Status. 35th AIAA Thermophysics Conference. AIAA 2001-3070. Anaheim, CA. 2001
[18]. R. K. Lobb. Experimental Measurement of Shock Detachment Distance on Spheres Fired in Air at Hyper Velocities. The High Temperature Aspects of Hypersonic Flow. Proc AGARD-NATO Specialist's Meeting, Belgium, 1962:519-527.
[19]. D. C. Reda. Correlation of Boundary-Layer Transition Data Measured in Ballistic-Range Experiments. SAND79-0649. UC-13, Sandia Lab., 1979
[20]. Satoshi Nonaka, Kazuyoshi Takayama, C. Park. Measurement of Shock Stand-off Distance for Sphere in Ballistic Range. 35(th) Aerospace Sciences Meeting & Exhibit. AIAA 97-0563. Reno, NV. January 6-10, 1997
[21]. Satoshi Nonaka, Kazuyoshi Takayama. Overview of Ballistic Range Program at Tohoku University. AIAA 98-2604. 1998
[22]. Satoshi Nonaka, H. Mizuno, K. Takayama. Ballistic Range Measurement of Shock Spheres in Intermediate Hypersonic Regime. 37(th) AIAA Aerospace Sciences Meeting and Exhibit. AIAA 99-1025. Reno, NV. 1999
[23]. J. S. Shang, J. R. Hayes, J. H. Miller. Magneto-Aerodynamic Interactions in Weakly Ionized Hypersonic Flow. AIAA 2002-0349. 2002
[24]. Heard Lowry, Chip Stepanek, Les Crosswy, etc. Shock Structure of a Spherical Projectile in Weakly Ionized Air. AIAA 99-0600. 1999
[25]. George. R. Inger, Charlotte Higgins, Richard Morgan. Generalized Nonequilibrium Binary Scaling for Shock Standoff on Hypersonic Blunt Bodies. AIAA 2002-1117. 2002
[26]. George R. Inger, Charlotte Higgins, Richard Morgan. Shock Standoff on Hypersonic Blunt Bodies in Nonequilibrium Gas Flows. AIAA 2001-0812. 2001
[27]. Akiko Matsuo. Instability of Projectile-Induced Combustion. 40(th) AIAA Aerospace Sciences Meeting & Exhibit. AIAA 2002-0775. Reno, Nevada. January 14-17, 2002
[28]. K. Donohue, W. J. Marinelli, R. H. Krech and G. E. Caledonia. Studies of Non-Equilibrium Radiation Signatures Behind Hypersonic Shock Fronts. AIAA 92-2869. 1992
[29]. Nai-Yi Zhu, Ai-Min Ren, Zhao-Ning Li, and Qian-Suo Yang. Investigation of Nonequilibrium Radiation and Relaxation Phenomena in Shock Tubes. AIAA 98-2468. 1998
[30]. R. I. Primich, M. Steinberg. A Broad Survey of Free-Flight Range Measurements from The Flow About Spheres and Cones. GM Defense Research Laboratories. TR63-224. Santa Barbara, California. September 1963
[31]. K. L. Dietz, K. S. Beale, W. K. McGregor. Ultraviolet/Visible Spectral Radiation from the Nose Cap of a Projectile Launched in a Ballistic Range [R]. AIAA 90-1552. 1990
[32]. X. Y. Chang, M. Hemmi, K. Komurasaki, T. Fujiwara. Radiation Measurements by Using a Ballistic Range [R]. AIAA 93-0635. 1993
[33]．葛学真，赵成修，竺乃宜，张正信．弹道靶红外辐射测量[J]．流体力学实验与测量，2002，16(1)：74-79(GE Xue-zhen, ZHAO Cheng-xiu, ZHU Nai-yi, ZHANG Zheng-xin. The Measurement of Infrared Radiation for Ballistic Range [J]. Experiments and Measurements in Fluid Mechanics. 2002, 16(1): 74-79 (In Chinese))
[34]. Bonnie J. McBride, Sanford Gordon. Computer Program for Calculation of Complex Chemical Equilibrium Compositions and Applications. NASA Reference Publication 1311. June 1996
[35]. Laurent Dala. Van Leer Flux-Splitting Algorithm for Nonequilibrium Flows Including Vibrational Relaxation. AIAA 99-4839. 1999
[36]. Sung-soo Kim, Chongam Kim, Oh-hyun Rho. Multigrid Algorithm for Computing Hypersonic, Chemically Reacting Flows. Journal of Spacecraft and Rockets. 2001,38(6):865～874
[37]. Ramadas K. Prabhu. An Implementation of a Chemical and Thermal Nonequilibrium Flow Solver on Unstructured Meshes and Application to Blunt Bodies. NASA Contractor Report 194967. August 1994
[38]. R. L. Lee, A. Hosangadi, B. J. York. Applocations of an unstructured solver to reactive, multiphase plume/propulsive flowfields. 32(nd) AIAA/ASME/SAE/ASEE Joint Propulsion Conference. AIAA 96-2955. Lake Buena Vista, FL. July 1-3, 1996
[39]. Seong-lyong Kim, Jeong-yeol Choi. Approximate Jacobian Methods for Efficient Calculation of Reactive Flows. 36(th)AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. AIAA 2000-3384. Huntsville, Alabama. July 17-19, 2000
[40]. Philippe Montarnal, Chi-Wang Shu. Real Gas Computation Using an Energy Relaxation Method and High-order WENO Schemes. ICASE Report No. 98-42. 1998
[41]. T. J. Millar, P. R. A. Farquhar, K. Willacy. The UMIST database for astrochemistry 1995. Astron. Astrophys. Supplement Series 121, 1997:139-185
[42]．姜宗林．爆轰推进概念与机理研究—新型发动机研究的热点．第十届全国激波与激波管学术讨论会论文集．安徽黄山，2002：29～37
[43]. Ian Alexander Johnston. Simulation of Flow Around Hypersonic Blunt-Nosed Vehicles for the Calibration of Air Data Systems. Thesis of PHD. Department of Mechanical Engineering, The University of Queensland. January 1999
[44]．欧阳水吾，谢中强．非平衡化学反应流场NS方程计算研究．计算物理．1997，14(1)：6-12 (Ou Yang Shui-wu, Xie Zhong-qiang. Navier-Stokes Computation of Nonequilibrium Chemically Reacting Flowfields. Chinese Journal of Computational Physics. 1997,14(1):6-12. (In Chinese))
[45]．黄华，瞿章华．11组元轴对称热化学非平衡流场的数值求解．空气动力学学报．1999，17(4)：462-465．(Huang hua, Qu Zhang-hua. Numerical Study for Symmetric Thermochemical Nonequilibrium Flowfield with Eleven Species Air Model. ACTA AERODYNAMICA SINICA. 1999,17(4):462-465 (In Chinese))
[46]．董维中．气体模型对高超声速再入钝体气动参数计算影响的研究．空气动力学学报．2001，19(2)：197～202(Dong Wei-zhong. Thermal and Chemical Model Effect on the Calculation of Aerodynamic Parameter for Hypersonic Reentry Blunt Body. ACTA AERODYNAMICA SINICA. 2001,19(2): 197～202 (In Chinese))
[47]. C. Park. Nonequilibrium Hypersonic Aerothermodynamics. John Wiley & Sons Inc, 1990
[48]. Chul Park. Nonequilibrium Air Radiation (NEQAIR) Program: User's Manual. NASA-TM-86707, July 1985
[49]. C. O. Laux, T. G. Spence, C. H. Kruger and R. N. Zare. Optical diagnostics of atmospheric pressure air plasmas. Institude of Physics Publishing. Plasma Sources Science and Technology. 2003,12:125～138
[50]. S. Kanne, T. H. Gogel, M. Dupuis, E. W. Messerschmid. Simulation of Radiation Experiments on Reentry Vehicles Using the New Radiation Database PARADE. AIAA 97-2562. 1997
[51]. J. W. L. Lewis, C. G. Parigger, J. O. Hornkohl, G. Guan. Laser-Induced Optical. Breakdown Plasma Spectra and Analyses with the Program NEQAIR. 37th Aerospace Sciences Meeting & Exhibit. AIAA-99-0723. Reno, NV. January 11-14, 1999
[52]．张锁春．辐射流体力学计算中的一个特殊问题．力学学报．1985，17(4)
[53]．瞿章华，沈建伟，杨宏．高超声速化学平衡流辐射流场数值解．宇航学报．1994，15(1)：87～91
[54]．周学华，竺乃宜．高超声速小钝锥尾流非平衡辐射研究．空气动力学学报．1996，14(3)
[55]．沈建伟，瞿章华．电离非平衡粘性激波层低雷诺数钝体绕流．空气动力学学报．1986，4(4)
[56]．薛君敖，李在清，朴大植，孟昭仟．光辐射测量原理和方法．北京：中国计量出版社，1981：4，45
[57]．柳军，乐嘉陵，杨辉．高超声速圆球模型飞行流场的数值模拟和实验验证．流体力学实验与测量，2002，16(1)：67-73(Liu Jun, Le Jialing, Yang Hui. Numerical Simulation of Hypersonic Flowfield Around Sphere Model and Experimental Verification. Experiments and Measurements in Fluid Mechanics, 2002, 16(1): 67-73 (in Chinese))
[58]. M. Furudate, S. Nonaka and K. Sawada. Behavior of Two-Temperature Model in Intermediate Hypersonic Regime. 37(th) AIAA Aerospace Sciences Meeting and Exhibit. AIAA 99-0223. Reno, NV. Jan. 1999
[59]．周书铨．高等学校教材：红外辐射测量基础．1991：113，114
[60]．[美]F．格鲁姆R．J．贝彻雷．辐射度学．1987：236
[61]．何圣静主编．物理实验手册．北京：机械工业出版社，1989：637，798
[62]. S. G. Rock, G. V. Candler, H. G. Homung. Analysis of Thermo-Chemical Nonequilibrium Models for Carbon Dioxide Flows. AIAA 27(th) Thermophysice Conference. AIAA 92-2852. Nashville, TN. July 6-8, 1992
[63]. G.. V. Candler, J. Olejiniczak. Nitrogen Dissociation Rates in Complex Hypersonic Flows. 32(nd) Thermophysics Conference. AIAA 97-2500. Atlanta, GA. June 23-25, 1997
[64]. Keisuke Sawada, Eishin Dendou. Validation of Hypersonic Equilibrium Flow Calculations Using Ballistic-range Data. 35(th) AIAA Aerospace Sciences Meeting & Exhibit. AIAA 97-0344. Reno, Nevada. January 6-10, 1997
[65]. Michiko Furudate, Toshiyuki Suzuki, Keisuke Sawada. Calculation of Intermediate Hypersonic Flow Using Multi-Temperature Model. 38(th) AIAA Aerospace Sciences Meeting & Exhibit. AIAA 2000-0343. Reno, Nevada. January 10-13, 2001
[6
[66]. Michiko Furudate, Toshiyuki Suzuki, Keisuke Sawada. Vibration-dissociation Coupling Effects on Shock Standoff Distances. 34(th) AIAA Thermo physics Conference. AIAA 2000-2499. Denver, CO. June 19-22, 2000
[67]. Michiko Furudate, Keisuke Sawada. Effect of Rotational Nonequilibrium on Shock Standoff Distances in Intermediate Hypersonic Range. 39(th) AIAA Aerospace Sciences Meeting & Exhibit. AIAA 2001-0813. Reno, Nevada. January 8-11, 2001
[68]. Henri-Marie Damevin, Klaus A. Hoffmann. Computation of Hypersonic, Chemically Reacting Magneto-gasdynamic Flows over a Cylinder. 40(th) AIAA Aerospace Sciences Meeting & Exhibit. AIAA 2002-0648. Reno, Nevada. January 14-17, 2002
[69]. Charles H. Campbell, Graham V. Candler. Detailed Simulation of Nitrogen Dissociation Over a Sphere. 38(th) AIAA Aerospace Sciences Meeting & Exhibit. AIAA 2000-0212. Reno, Nevada. January 10-13, 2001
[70]. Park C. Problems of Rate Chemistry in the Flight Regimes of Aeroassisted Orbital Transfer Vehicles. Progress in Astronautics and Aeronautics. 1985, 96:511～537
[71]. Peter A. Gnoffo, L. Shinn, Roop N. Gupta. Conservation Equations and Physical Models for Hypersonic Air Flows in Thermal and Chemical Nonequilibrium. NASA TP-2867,1989
[72]．瞿章华．不同扩散模型对再入体等离子体鞘电子密度分布的影响．国防科技大学学报．1993年9月
[73]. W. G. Vincenti and C. H. Kruger. Introduction to Physical Gas Dynamics. Robert E. Krieger Publishing Company. 1965
[74]. C. Frederick Hansen. Approximations for the thermodynamic and transport properties of high-temperature air. NASA TR-R50. 1959
[75]. J. C. Tannehill, P. H. Mugge. Improved Curve Fits for The Thermodynamic Properties of Equilibrium Air Suitable for Numerical Computation Using Time-dependent or Shock-capturing Methods. NASA CR-2470. 1974
[76]. Yen Liu. Marcel Vinokur. Equilibrium Gas Flow Computations. I. Accurate and Efficient Calculation of Equilibrium Gas Properties. AIAA 24(th) Thermophysics Conference. AIAA 89-1736. Buffalo, New York. June 12-14, 1989
[77]. M. Gazaix. Hypersonic Inviscid and Viscous Flow Computations with A New Optimized Thermodynamic Equilibrium Model. 31(ST) Aerospace Sciences Meeting & Exhibit. AIAA 93-0893. Reno, NV. January 11-14,1993
[78]. Wilmer Neuenschwander. Explicit Relationships for the Thermodynamic Properties of Molecular and Dissociated Air Mixtures to 25,000 Degree R. AIAA 24(th) Thermophysics Conference. AIAA 89-1735. Buffalo, New York. June 12-14,1989
[79]. S. Srinivasan, J. C. Tannehill, K. J. Weilmuenster. Simplified Curve Fits for The Thermodynamic Properties of Equilibrium Air. NASA RP-1181.1987
[80]. S. Srinivasan, J. C. Tannehill. Simplified Curve Fits for The Transport Properties of Equilibrium Air. NASA CR-178411. 1987
[81]. Roop N. Gupta, Kam-Pui Lee, Richard A. Thompson, Jerrold M. Yos. Calculations and Curve Fits of Thermodynamic and Transport Properties for Equilibrium Air to 30000K. NASA RP-1260. 1991
[82]. Gunnar O. Einarsson. Evaluation of Thermochemical Models for Aerocapture Re-entries. 37th AIAA Aerospace Sciences Meeting an Exhibit. AIAA 99-0015. Reno, NV. January 11-14, 1999
[83]. M. H. Bortner. Suggested Standard Chemical Kinetics for Flow Field Calculations—A Consensus Opinion. AMRAC Proceedings. Volume ⅩⅣ. Part Ⅰ. Doe. No. 4613-135-X (Contract SD-91). Inst. of Science and Technology. Univ. of Michigan. Apr. 18-19. 1966:569-581 (Available from DTIC as AD 372 900)
[84]. M. G. Dunn, S. W. Kang. Theoretical and Experimental Studies of Reentry Plasmas. NASA CR-2232. 1973
[85]. C. Park. Assessment of Two-Temperature Kinetic Model for Ionizing Air. In AIAA 22nd Thermophysics Conference. AIAA paper 87-1574. Honolulu, Hawaii, June 1987
[86]. Chul Park, Richard L. Jaffe, Harry Partridge. Chemical-Kinetic Parameters of Hyperbolic Earth Entry. Journal of Thermophysics and heat transfer. 2001,15(1):76-89. January-March 2001
[87]．董维中．热化学非平衡效应对高超声速流动影响的数值计算与分析．北京航空航天大学研究生院博士学位论文．1996(Dong Wei-zhong． Numerical Simulation and Analysis of Thermochemical Nonequilibrium Effects at Hypersonic Flow. Ph D Thesis. Beijing University of Aeronautics and Astronautics. 1996(In Chinese))
[88]. L. M. G. F. Walpot. LORE: Description and Validation of a New Developed Three-dimensional Thermo-chemical Nonequilibrium Navier-Stokes Solver. Memorandum M-815. Faculty of Aerospace Engineering, TUDelft. Oct. 1997
[89]. R. C. Millikan, D. R. White Systematics of Vibrational Relaxation. Journal of Chemical Physics. 1963,39(12):3209-3213
[90]. M. Capitelli, C. Gorse, S. Longo, D. Giordano. Transport Properties of High Temperature Air Species. AIAA 98-2936. 1998
[91]. M. Fertig, A. Dohr, H.-H. Fr(?)hauf. Transport Coefficients for High Temperature Nonequilibrium Air Flows. AIAA 98-2937. 1998
[92]. Stefan Selle, Uwe Riedel. Transport Coefficients of Reacting Air at High Temperatures. 38th Aerospace Sciences Meeting & Exhibit. AIAA 2000-0211. Reno, NV. January 10-13, 2000
[93]. F. C. Blottner. Chemically Reacting Viscous Flow Program for Component Gas Mixtures. Sandia Lab. Rept, SC-RR-70-754, Dec. 1971
[94]. William A. Wood, Scott Eberhardt. Dual-Code Solution Strategy for Chemically-Reacting Hypersonic Flows. AIAA 95-0158.1995
[95]. G. V. Candler, R. W. MacCormack. The Computation of Hypersonic Ionized Flows in Chemical and Thermal Nonequilibrium. AIAA 88-0511. 1988
[96]. Ramadas K. Prabhu. An Approximate Riemann Solver For Thermal and Chemical Nonequilibrium Flows. NASA CR 195003.1995
[97]．赵兴艳，苏莫明，苗永淼．高分辨率激波捕捉格式及其CFD应用．计算物理．2001，18(2)：133-137 (ZHAO Xing-yan, SU Mo-ming, MIAO Yong-miao. High-resolution Shock-capturing Scheme and Its Application in CFD. Chinese Journal of Computational Physics. 2001,18(2):133-137 (In Chinese.))
[98]. J.-Ch. Robinnet, J. Gressier, G. Casalis, J.-M. Moschetta. Shock Wave Instability and the Carbuncle Phenomenon: Same Intrinsic Origin? J. Fluid Mech. 2000,417:237-263
[99]. M. S. Liou, Jr., C. J. Steffen. A New Flux Splitting Scheme. Journal of Computational Physics. 1993, 107:23-39
[100]. S. Aso, K. Hayashi, M. Mizoguchi. A Study on Aerodynamic Heating Reduction due to Opposing Jet in Hypersonic Flow. 40th AIAA Aerospace Sciences Meeting & Exhibit. AIAA 2002-0646. Reno, NV. January 14-17, 2002
[101]. Meng-Sing Liou, Pieter G. Buning. Contribution of The Recent AUSM Schemes to The Overflow Code: Implimentation and Validation. AIAA 2000-4404. 2000
[102]. Hirotaka Otsu, Akihiro Sasoh, Kazuhisa Fujita, Takashi Abe. Assessment of the Thermochemical Model for a Super-orbital Reentry Flow. 8(th) AIAA/ASME Joint Thermophysics and Heat Transfer Conference. AIAA 2002-3310. St. Louis, Missouri. June 24-26, 2002
[103]. M. Kaneko, I. Menshov. Y. Nakamura. Reflected Shock Wave/Boundary Layer Interaction in High-Enthalpy Shock Tunnel. AIAA 2000-2600. 2000
[104]. Yang-Yao Niu. Numerical Simulation of Dynamic Stall Using Upwind Methods and RNG Turbulence Models. AIAA 98-0419. 1998
[105]. Yang-Yao Niu. On Some Simple and Robust Riemann Solvers for Compressible Two-Phase Flows. 15th AIAA Computational Fluid Dynamics Conference. AIAA-2001-2647. Anaheim, CA. June 11-14, 2001
[106]. Munetsugu Kaneko, Igor Menshov, Yoshiaki Nakamura. Computation of Nozzle Starting Process with Thermal and Chemical Nonequilibrium in High-Enthalpy Shock Tunnel. 40(th) AIAA Aerospace Sciences Meeting & Exhibit. AIAA 2002-0142. Reno, NV. Jan 14-17, 2002
[107]. R. Agarwal, J. Augustinus. A Comparative Study of Advection Upwind Split (AUSM) and Wave/Particle Split (WPS) Schemes for Fluid and MHD Flows. 30th Plasmadynamics and Lasers Conference. AIAA 99-3613. Norfolk, VA. June 28-July 1, 1999
[108]．张涵信．无波动，无自由参数的耗散差分格式．空气动力学报，1988，6(1)
[109]. Shen Qing. Zhang Hanxin. A New Upwind NND Scheme for Euler Equations and Its Application to The Supersonic Flow. Proceedings of Asia Workshop on CFD. Sichuan, China. September 12, 1994
[110]. Joon Ho Lee, Oh Hyun Rho. Numerical Analysis of Hypersonic Viscous Flows Around a Blunt Body Using Roe's FDS and AUSM+ schemes. 28(th) AIAA Fluid Dynamics Conference and 4(th) AIAA Shear Flow Control Conference. AIAA Paper 97-2054. Snowmass Village, CO. June 29-July 2,1997
[111]. Joon Ho Lee, Oh Hyun Rho. Accuracy of AUSM+ Scheme in Hypersonic Blunt Body Flow Calculations. AIAA 98-1538.1998
[112]. K. H. Kim, O. H. Rho. An Improvement of AUSM Schemes by Introducing The Pressure-Based Weight Functions. The fifth Annual Conference of the Computational Fluid Dynamics Society of Canada (CFD 97). 1997: (14-33)-(14-38).
[113]. Kyu Hong Kim, Joon Ho Lee, Oh Hyun Rho. An Improvement of AUSM Schemes by Introducing The Pressure-Based Weight Functions. Computers & Fluids. 1998, 27(3):311-346
[114]. Kyu Hong KIM, Chongam KIM, Oh Hyun RHO. Accurate Computations of Hypersonic Flows Using AUSMPW+ Scheme and Shock-Aligned Grid Technique. AIAA 98-2442. 1998
[115]. Thomas. R. A. Bussing, Earll M. Murman. Finite-Volume Method for the Calculation of Compressible Chemically Reacting Flows. AIAA J. 1988,. 26(9): 1070-1078
[116]. Shigeru Aso, Takuji Kurotaki, Yoshiyuki Miyamoto. Experimental and Computational Study on Reduction of Aerodynamic Heating Load by Film Cooling in Hypersonic Flows. AIAA 97-0770. 1997
[117]. P. Stoll, P. Gerlinger, D. Br(?)ggemann. Domain Decomposition for an Implicit LU-SGS Scheme using Overlapping Grids. AIAA 97-1896. 1997
[118]．柳军．飞船返回舱三维化学非平衡流全流场数值模拟．国防科技大学研究生院硕士学位论文．2000年3月
[119]. Le Jia-ling, Wu Ying-chuan et al. Computational Interferometry for Three-Dimension Flow. Experiments and Measurements in Fluid Mechanics. 2001, 15(2)
[120]．卞荫贵，徐立功．气动热力学．合肥：中国科学技术大学出版社，1997：156
[121]. Luen T. Tam, Michael Y. An, Charles H. Campbell. Nonequilibrium Hypersonic Flow Computation for Weakly Ionized Air and Comparison with Flight Data, AIAA 24(th) Plasmadynamics & Lasers Conference. AIAA 93-3195. Orlando, FL. July 6-9, 1993
[122]．黄华，瞿章华．飞船轴对称热化学非平衡流场数值求解．国防科技大学学报．1999，21(3)：1-4 (Huang hua. Qu zhang-hua. Axial Symmetric Numerical Simulation of Thermochemical Nonequilibrium Flow over Spaceship. Journal of National University of Defense Technology. 1999, 21 (3):1-4 (In Chinese))
[123]．欧阳水吾，谢中强．近代空气动力学丛书：高温非平衡空气绕流．北京：国防工业出版社．2001
[124]．柳军，曾明，瞿章华．飞船再入舱三维化学非平衡流数值模拟。国防科技大学学报．1999，21(6)：9-12 (Liu Jun. Zeng Ming. Qu Zhang-hua. Numerical Simulation of Three Dimensional Chemical Nonequilibrium Flow over The Reentry Vehicle. Journal of National University of Defense Technology. 1999, 21(6):9-12 (In Chinese))
[125]．袁先旭．非定常流动数值模拟及飞行器动态特性分析研究．中国空气动力研究与发展中心博士学位论文．2002
[126]. Roger Peyret, Handbook of Computational Fluid Mechanics, Academic Press Limited, 1996
[127]. S. K. Saxena, K. Ravi, Some Aspects of High-Speed Blunt Body Flow Computations with Roe Scheme, AIAA Journal. 1995, Vol.33(6)
[128]．黎作武．含激波旋涡和化学非平衡反应的高超音速复杂流场的数值模拟．中国空气动力研究与发展中心博士学位论文．1995
[129]. D. B. Wilkinson. Hypersonic Shock Tunnel Tests of the .05 Scale Apollo Force Model. FS-8, Cornell Aeronautical Laboratory Report AA-1712-W-1 (Prime NASA Apollo Contract NAS 9-150), Buffalo, NY, Oct. 1962
[130]. B. Hassan, G. V. Candler, D. R. Olynick. The Effect of Thermo-Chemical Nonequilibrium on the Aerodynamics of Aero braking Vehicles. AIAA 92-2877. 1992
[131]．泽尔道维奇，莱依捷尔．力学名著译丛：激波和高温流体动力学现象物理学(上册)．北京，科学出版社，1980：115，353，265，274，277，302，308，336，338
[132]．章冠人．光子流体动力学理论基础．1996．55
[133]. George W. Sutton, Arthur Sherman. Engineering Magnetohydrodynamics. Me Graw-Hill Book Company, New York.
[134]. L. C. Hartung. Predicting Radiation Heat Transfer in Thermochemical Nonequilibriun Flow Fields. N95-11936. 1995
[135]. J. O. Arnold, D. M. Cooper, Chul Park. Line-by-Line Transport Calculations for Jupiter Entry Probes. AIAA 79-1082. 1979
[136]．吴国祯．分子振动光谱学基础．北京：化学工业出版社，1990
[137]．林美荣，张包铮．原子光谱学导论．北京：科学出版社，1990
[138]. J. O. Arnold, E. E. Whiting, G. C. Lyle. Line by Line Calculation of Spectra from Diatomic Molecules and Atoms Assuming A Voigt Line Profile, J. Quant. Spectrose. Radiant. Transfer. 1969, 9.775-798
[139]. Kovacs, Istvan. Rotational Structure in Spectra of Diatomic Molecules. Adam Hilger Ltd, London, 1969
[140]．[加]G．赫兹堡．分子光谱与分子结构：第一卷双原子分子光谱．王鼎昌译．北京：科学出版社，1983：14，68，110，152，159，163．
[141]. A. W. Ali Excitation and Ionization Crosections for Electron Beam and Microwave Energy Deposition in Air. Memorandum Report 4598, Naval Research Laboratory, Washington, D. C. Feb. 1982
[142]. S. Slinkers, A. W. Ali. Electron Excitation and Ionization Rate Coefficients for N2,O2,NO,N, and O. Memorandum Report 4756, Naval Research Laboratory, Washington, D. C. Feb. 1982
[143]. C. Park. Calculation of Nonequilibrium Radiation in AOTV Flight Regimes. AIAA 84-0306,1984
[144]．黄祖洽，丁鄂江．现代物理学丛书：输运理论．北京：科学出版社．1987
[145]. C. D. Engle, R. C. Farmer. Ablation and Radiation Coupled Viscous Hypersonic Shock Layer. NASA Grant NGR 19-001059, 1971
[146]．郭正．包含运动边界的多体非定常流场数值模拟方法研究．国防科技大学研究生院博士学位论文．2002
[147]. J. J. Bertin. Hypersonic Aerothermodynamics. AIAA, Washington DC. 1994
[148]．吴家驹译．科学图书大库：工程师用图表便览．台北市徐氏基金会．1978
[149]．瞿章华等．高超声速空气动力学．第二版．国防科技大学出版社，2001
[150]．黄华．耦合辐射的非平衡流场数值研究[学位论文][D]．湖南长沙：国防科技大学研究生院．1999(Huang Hua. Numerical Study of Nonequilibrium Flowfield Coupled with Radiation: [D]. Hunan Changsha: Graduate School of NUDT. 1999 (In Chinese)).
[151]．曹文祥．再入体尾流光辐射工程计算方法．CARDC技术报告．1984
[2]. Devendra S. Parmar, Qamar A. Shams. Aerothermal Instrumentation Loads to Implement Aeroassist Technology in Future Robotic and Human Missions to MARS and Other Locations Within the Solar System. NASA/TM-2002-211459. April 2002.
[3]． 黄志澄．高超声速飞行器空气动力学．北京：国防工业出版社，1995
[4]. R. A. Mercier, M. F. Ronald. Hypersonic Technology (HyTech) Program Overview. AIAA 98-1566, 1998
[5]. C. Rothmund, D. Scherrer Propulsion System for Airbreathing Launcher in the French PREPHA Program. AIAA 96-4498, 1996
[6]. M. Bouchez Scramjet Combustor Design in French PREPHA Program-Status in 1996. AIAA 96-4582, 1996
[7]. M. Bouchez, X. Montazel. Hydrocarbon-Fueled Airbreathing Propulsion for High Speed Missiles. AIAA 98-3729, 1998
[8]. W. W. Koschel. Basic Hypersonic Propulsion Research in German University. AIAA 98-1634, 1998
[9]. M. Kallenberg, E. Von Lavante. The Dynamics of Unsteady Supersonic Combustion. AIAA 98-3319, 1998
[10]. M. Maita, H. Kubota., Y. Moriguchi. Japanese Spaceplane/RLV Programme. IAF 97-V.4.05,1997
[11]. A. R. Srikrishan, J. Kurian, V. Sriramulu. A Comparative Experimental Study of Supersonic Combustion. ISABE 99-7055, 1999
[12]. F. Nasuti, M. Onofri. Numerical Analysis of the Slipstream Effect in Extemal Expansion Nozzle. ISABE 99-7122, 1999
[13]. R. N. Gupta, J. M. Yos, R. A. Thompson. A review of Reaction Rates and Thermodynamic and Transport Properties for an 11-species Air Model for Chemical and Thermal Non-equilibrium Calculations to 30000K. NASA RP 1232, 1990
[14]． 徐根兴主编．导弹与航天丛书(防空导弹系列)：目标和环境的光学特性．北京：宇航出版社，1995
[15]． 王福恒，王嵩薇．近代科学技术中的原子分子辐射理论．成都：成都科技大学出版社，1990：17，22，25，42
[16]．吴颖川．计算光学流动显示技术的研究与应用．中国空气动力研究与发展中心博士学位论文．2003年6月
[17]. Chul Park. Stagnation-Point Radiation for Apollo 4-A Review and Current Status. 35th AIAA Thermophysics Conference. AIAA 2001-3070. Anaheim, CA. 2001
[18]. R. K. Lobb. Experimental Measurement of Shock Detachment Distance on Spheres Fired in Air at Hyper Velocities. The High Temperature Aspects of Hypersonic Flow. Proc AGARD-NATO Specialist's Meeting, Belgium, 1962:519-527.
[19]. D. C. Reda. Correlation of Boundary-Layer Transition Data Measured in Ballistic-Range Experiments. SAND79-0649. UC-13, Sandia Lab., 1979
[20]. Satoshi Nonaka, Kazuyoshi Takayama, C. Park. Measurement of Shock Stand-off Distance for Sphere in Ballistic Range. 35(th) Aerospace Sciences Meeting & Exhibit. AIAA 97-0563. Reno, NV. January 6-10, 1997
[21]. Satoshi Nonaka, Kazuyoshi Takayama. Overview of Ballistic Range Program at Tohoku University. AIAA 98-2604. 1998
[22]. Satoshi Nonaka, H. Mizuno, K. Takayama. Ballistic Range Measurement of Shock Spheres in Intermediate Hypersonic Regime. 37(th) AIAA Aerospace Sciences Meeting and Exhibit. AIAA 99-1025. Reno, NV. 1999
[23]. J. S. Shang, J. R. Hayes, J. H. Miller. Magneto-Aerodynamic Interactions in Weakly Ionized Hypersonic Flow. AIAA 2002-0349. 2002
[24]. Heard Lowry, Chip Stepanek, Les Crosswy, etc. Shock Structure of a Spherical Projectile in Weakly Ionized Air. AIAA 99-0600. 1999
[25]. George. R. Inger, Charlotte Higgins, Richard Morgan. Generalized Nonequilibrium Binary Scaling for Shock Standoff on Hypersonic Blunt Bodies. AIAA 2002-1117. 2002
[26]. George R. Inger, Charlotte Higgins, Richard Morgan. Shock Standoff on Hypersonic Blunt Bodies in Nonequilibrium Gas Flows. AIAA 2001-0812. 2001
[27]. Akiko Matsuo. Instability of Projectile-Induced Combustion. 40(th) AIAA Aerospace Sciences Meeting & Exhibit. AIAA 2002-0775. Reno, Nevada. January 14-17, 2002
[28]. K. Donohue, W. J. Marinelli, R. H. Krech and G. E. Caledonia. Studies of Non-Equilibrium Radiation Signatures Behind Hypersonic Shock Fronts. AIAA 92-2869. 1992
[29]. Nai-Yi Zhu, Ai-Min Ren, Zhao-Ning Li, and Qian-Suo Yang. Investigation of Nonequilibrium Radiation and Relaxation Phenomena in Shock Tubes. AIAA 98-2468. 1998
[30]. R. I. Primich, M. Steinberg. A Broad Survey of Free-Flight Range Measurements from The Flow About Spheres and Cones. GM Defense Research Laboratories. TR63-224. Santa Barbara, California. September 1963
[31]. K. L. Dietz, K. S. Beale, W. K. McGregor. Ultraviolet/Visible Spectral Radiation from the Nose Cap of a Projectile Launched in a Ballistic Range [R]. AIAA 90-1552. 1990
[32]. X. Y. Chang, M. Hemmi, K. Komurasaki, T. Fujiwara. Radiation Measurements by Using a Ballistic Range [R]. AIAA 93-0635. 1993
[33]．葛学真，赵成修，竺乃宜，张正信．弹道靶红外辐射测量[J]．流体力学实验与测量，2002，16(1)：74-79(GE Xue-zhen, ZHAO Cheng-xiu, ZHU Nai-yi, ZHANG Zheng-xin. The Measurement of Infrared Radiation for Ballistic Range [J]. Experiments and Measurements in Fluid Mechanics. 2002, 16(1): 74-79 (In Chinese))
[34]. Bonnie J. McBride, Sanford Gordon. Computer Program for Calculation of Complex Chemical Equilibrium Compositions and Applications. NASA Reference Publication 1311. June 1996
[35]. Laurent Dala. Van Leer Flux-Splitting Algorithm for Nonequilibrium Flows Including Vibrational Relaxation. AIAA 99-4839. 1999
[36]. Sung-soo Kim, Chongam Kim, Oh-hyun Rho. Multigrid Algorithm for Computing Hypersonic, Chemically Reacting Flows. Journal of Spacecraft and Rockets. 2001,38(6):865～874
[37]. Ramadas K. Prabhu. An Implementation of a Chemical and Thermal Nonequilibrium Flow Solver on Unstructured Meshes and Application to Blunt Bodies. NASA Contractor Report 194967. August 1994
[38]. R. L. Lee, A. Hosangadi, B. J. York. Applocations of an unstructured solver to reactive, multiphase plume/propulsive flowfields. 32(nd) AIAA/ASME/SAE/ASEE Joint Propulsion Conference. AIAA 96-2955. Lake Buena Vista, FL. July 1-3, 1996
[39]. Seong-lyong Kim, Jeong-yeol Choi. Approximate Jacobian Methods for Efficient Calculation of Reactive Flows. 36(th)AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. AIAA 2000-3384. Huntsville, Alabama. July 17-19, 2000
[40]. Philippe Montarnal, Chi-Wang Shu. Real Gas Computation Using an Energy Relaxation Method and High-order WENO Schemes. ICASE Report No. 98-42. 1998
[41]. T. J. Millar, P. R. A. Farquhar, K. Willacy. The UMIST database for astrochemistry 1995. Astron. Astrophys. Supplement Series 121, 1997:139-185
[42]．姜宗林．爆轰推进概念与机理研究—新型发动机研究的热点．第十届全国激波与激波管学术讨论会论文集．安徽黄山，2002：29～37
[43]. Ian Alexander Johnston. Simulation of Flow Around Hypersonic Blunt-Nosed Vehicles for the Calibration of Air Data Systems. Thesis of PHD. Department of Mechanical Engineering, The University of Queensland. January 1999
[44]．欧阳水吾，谢中强．非平衡化学反应流场NS方程计算研究．计算物理．1997，14(1)：6-12 (Ou Yang Shui-wu, Xie Zhong-qiang. Navier-Stokes Computation of Nonequilibrium Chemically Reacting Flowfields. Chinese Journal of Computational Physics. 1997,14(1):6-12. (In Chinese))
[45]．黄华，瞿章华．11组元轴对称热化学非平衡流场的数值求解．空气动力学学报．1999，17(4)：462-465．(Huang hua, Qu Zhang-hua. Numerical Study for Symmetric Thermochemical Nonequilibrium Flowfield with Eleven Species Air Model. ACTA AERODYNAMICA SINICA. 1999,17(4):462-465 (In Chinese))
[46]．董维中．气体模型对高超声速再入钝体气动参数计算影响的研究．空气动力学学报．2001，19(2)：197～202(Dong Wei-zhong. Thermal and Chemical Model Effect on the Calculation of Aerodynamic Parameter for Hypersonic Reentry Blunt Body. ACTA AERODYNAMICA SINICA. 2001,19(2): 197～202 (In Chinese))
[47]. C. Park. Nonequilibrium Hypersonic Aerothermodynamics. John Wiley & Sons Inc, 1990
[48]. Chul Park. Nonequilibrium Air Radiation (NEQAIR) Program: User's Manual. NASA-TM-86707, July 1985
[49]. C. O. Laux, T. G. Spence, C. H. Kruger and R. N. Zare. Optical diagnostics of atmospheric pressure air plasmas. Institude of Physics Publishing. Plasma Sources Science and Technology. 2003,12:125～138
[50]. S. Kanne, T. H. Gogel, M. Dupuis, E. W. Messerschmid. Simulation of Radiation Experiments on Reentry Vehicles Using the New Radiation Database PARADE. AIAA 97-2562. 1997
[51]. J. W. L. Lewis, C. G. Parigger, J. O. Hornkohl, G. Guan. Laser-Induced Optical. Breakdown Plasma Spectra and Analyses with the Program NEQAIR. 37th Aerospace Sciences Meeting & Exhibit. AIAA-99-0723. Reno, NV. January 11-14, 1999
[52]．张锁春．辐射流体力学计算中的一个特殊问题．力学学报．1985，17(4)
[53]．瞿章华，沈建伟，杨宏．高超声速化学平衡流辐射流场数值解．宇航学报．1994，15(1)：87～91
[54]．周学华，竺乃宜．高超声速小钝锥尾流非平衡辐射研究．空气动力学学报．1996，14(3)
[55]．沈建伟，瞿章华．电离非平衡粘性激波层低雷诺数钝体绕流．空气动力学学报．1986，4(4)
[56]．薛君敖，李在清，朴大植，孟昭仟．光辐射测量原理和方法．北京：中国计量出版社，1981：4，45
[57]．柳军，乐嘉陵，杨辉．高超声速圆球模型飞行流场的数值模拟和实验验证．流体力学实验与测量，2002，16(1)：67-73(Liu Jun, Le Jialing, Yang Hui. Numerical Simulation of Hypersonic Flowfield Around Sphere Model and Experimental Verification. Experiments and Measurements in Fluid Mechanics, 2002, 16(1): 67-73 (in Chinese))
[58]. M. Furudate, S. Nonaka and K. Sawada. Behavior of Two-Temperature Model in Intermediate Hypersonic Regime. 37(th) AIAA Aerospace Sciences Meeting and Exhibit. AIAA 99-0223. Reno, NV. Jan. 1999
[59]．周书铨．高等学校教材：红外辐射测量基础．1991：113，114
[60]．[美]F．格鲁姆R．J．贝彻雷．辐射度学．1987：236
[61]．何圣静主编．物理实验手册．北京：机械工业出版社，1989：637，798
[62]. S. G. Rock, G. V. Candler, H. G. Homung. Analysis of Thermo-Chemical Nonequilibrium Models for Carbon Dioxide Flows. AIAA 27(th) Thermophysice Conference. AIAA 92-2852. Nashville, TN. July 6-8, 1992
[63]. G.. V. Candler, J. Olejiniczak. Nitrogen Dissociation Rates in Complex Hypersonic Flows. 32(nd) Thermophysics Conference. AIAA 97-2500. Atlanta, GA. June 23-25, 1997
[64]. Keisuke Sawada, Eishin Dendou. Validation of Hypersonic Equilibrium Flow Calculations Using Ballistic-range Data. 35(th) AIAA Aerospace Sciences Meeting & Exhibit. AIAA 97-0344. Reno, Nevada. January 6-10, 1997
[65]. Michiko Furudate, Toshiyuki Suzuki, Keisuke Sawada. Calculation of Intermediate Hypersonic Flow Using Multi-Temperature Model. 38(th) AIAA Aerospace Sciences Meeting & Exhibit. AIAA 2000-0343. Reno, Nevada. January 10-13, 2001
[6
[66]. Michiko Furudate, Toshiyuki Suzuki, Keisuke Sawada. Vibration-dissociation Coupling Effects on Shock Standoff Distances. 34(th) AIAA Thermo physics Conference. AIAA 2000-2499. Denver, CO. June 19-22, 2000
[67]. Michiko Furudate, Keisuke Sawada. Effect of Rotational Nonequilibrium on Shock Standoff Distances in Intermediate Hypersonic Range. 39(th) AIAA Aerospace Sciences Meeting & Exhibit. AIAA 2001-0813. Reno, Nevada. January 8-11, 2001
[68]. Henri-Marie Damevin, Klaus A. Hoffmann. Computation of Hypersonic, Chemically Reacting Magneto-gasdynamic Flows over a Cylinder. 40(th) AIAA Aerospace Sciences Meeting & Exhibit. AIAA 2002-0648. Reno, Nevada. January 14-17, 2002
[69]. Charles H. Campbell, Graham V. Candler. Detailed Simulation of Nitrogen Dissociation Over a Sphere. 38(th) AIAA Aerospace Sciences Meeting & Exhibit. AIAA 2000-0212. Reno, Nevada. January 10-13, 2001
[70]. Park C. Problems of Rate Chemistry in the Flight Regimes of Aeroassisted Orbital Transfer Vehicles. Progress in Astronautics and Aeronautics. 1985, 96:511～537
[71]. Peter A. Gnoffo, L. Shinn, Roop N. Gupta. Conservation Equations and Physical Models for Hypersonic Air Flows in Thermal and Chemical Nonequilibrium. NASA TP-2867,1989
[72]．瞿章华．不同扩散模型对再入体等离子体鞘电子密度分布的影响．国防科技大学学报．1993年9月
[73]. W. G. Vincenti and C. H. Kruger. Introduction to Physical Gas Dynamics. Robert E. Krieger Publishing Company. 1965
[74]. C. Frederick Hansen. Approximations for the thermodynamic and transport properties of high-temperature air. NASA TR-R50. 1959
[75]. J. C. Tannehill, P. H. Mugge. Improved Curve Fits for The Thermodynamic Properties of Equilibrium Air Suitable for Numerical Computation Using Time-dependent or Shock-capturing Methods. NASA CR-2470. 1974
[76]. Yen Liu. Marcel Vinokur. Equilibrium Gas Flow Computations. I. Accurate and Efficient Calculation of Equilibrium Gas Properties. AIAA 24(th) Thermophysics Conference. AIAA 89-1736. Buffalo, New York. June 12-14, 1989
[77]. M. Gazaix. Hypersonic Inviscid and Viscous Flow Computations with A New Optimized Thermodynamic Equilibrium Model. 31(ST) Aerospace Sciences Meeting & Exhibit. AIAA 93-0893. Reno, NV. January 11-14,1993
[78]. Wilmer Neuenschwander. Explicit Relationships for the Thermodynamic Properties of Molecular and Dissociated Air Mixtures to 25,000 Degree R. AIAA 24(th) Thermophysics Conference. AIAA 89-1735. Buffalo, New York. June 12-14,1989
[79]. S. Srinivasan, J. C. Tannehill, K. J. Weilmuenster. Simplified Curve Fits for The Thermodynamic Properties of Equilibrium Air. NASA RP-1181.1987
[80]. S. Srinivasan, J. C. Tannehill. Simplified Curve Fits for The Transport Properties of Equilibrium Air. NASA CR-178411. 1987
[81]. Roop N. Gupta, Kam-Pui Lee, Richard A. Thompson, Jerrold M. Yos. Calculations and Curve Fits of Thermodynamic and Transport Properties for Equilibrium Air to 30000K. NASA RP-1260. 1991
[82]. Gunnar O. Einarsson. Evaluation of Thermochemical Models for Aerocapture Re-entries. 37th AIAA Aerospace Sciences Meeting an Exhibit. AIAA 99-0015. Reno, NV. January 11-14, 1999
[83]. M. H. Bortner. Suggested Standard Chemical Kinetics for Flow Field Calculations—A Consensus Opinion. AMRAC Proceedings. Volume ⅩⅣ. Part Ⅰ. Doe. No. 4613-135-X (Contract SD-91). Inst. of Science and Technology. Univ. of Michigan. Apr. 18-19. 1966:569-581 (Available from DTIC as AD 372 900)
[84]. M. G. Dunn, S. W. Kang. Theoretical and Experimental Studies of Reentry Plasmas. NASA CR-2232. 1973
[85]. C. Park. Assessment of Two-Temperature Kinetic Model for Ionizing Air. In AIAA 22nd Thermophysics Conference. AIAA paper 87-1574. Honolulu, Hawaii, June 1987
[86]. Chul Park, Richard L. Jaffe, Harry Partridge. Chemical-Kinetic Parameters of Hyperbolic Earth Entry. Journal of Thermophysics and heat transfer. 2001,15(1):76-89. January-March 2001
[87]．董维中．热化学非平衡效应对高超声速流动影响的数值计算与分析．北京航空航天大学研究生院博士学位论文．1996(Dong Wei-zhong． Numerical Simulation and Analysis of Thermochemical Nonequilibrium Effects at Hypersonic Flow. Ph D Thesis. Beijing University of Aeronautics and Astronautics. 1996(In Chinese))
[88]. L. M. G. F. Walpot. LORE: Description and Validation of a New Developed Three-dimensional Thermo-chemical Nonequilibrium Navier-Stokes Solver. Memorandum M-815. Faculty of Aerospace Engineering, TUDelft. Oct. 1997
[89]. R. C. Millikan, D. R. White Systematics of Vibrational Relaxation. Journal of Chemical Physics. 1963,39(12):3209-3213
[90]. M. Capitelli, C. Gorse, S. Longo, D. Giordano. Transport Properties of High Temperature Air Species. AIAA 98-2936. 1998
[91]. M. Fertig, A. Dohr, H.-H. Fr(?)hauf. Transport Coefficients for High Temperature Nonequilibrium Air Flows. AIAA 98-2937. 1998
[92]. Stefan Selle, Uwe Riedel. Transport Coefficients of Reacting Air at High Temperatures. 38th Aerospace Sciences Meeting & Exhibit. AIAA 2000-0211. Reno, NV. January 10-13, 2000
[93]. F. C. Blottner. Chemically Reacting Viscous Flow Program for Component Gas Mixtures. Sandia Lab. Rept, SC-RR-70-754, Dec. 1971
[94]. William A. Wood, Scott Eberhardt. Dual-Code Solution Strategy for Chemically-Reacting Hypersonic Flows. AIAA 95-0158.1995
[95]. G. V. Candler, R. W. MacCormack. The Computation of Hypersonic Ionized Flows in Chemical and Thermal Nonequilibrium. AIAA 88-0511. 1988
[96]. Ramadas K. Prabhu. An Approximate Riemann Solver For Thermal and Chemical Nonequilibrium Flows. NASA CR 195003.1995
[97]．赵兴艳，苏莫明，苗永淼．高分辨率激波捕捉格式及其CFD应用．计算物理．2001，18(2)：133-137 (ZHAO Xing-yan, SU Mo-ming, MIAO Yong-miao. High-resolution Shock-capturing Scheme and Its Application in CFD. Chinese Journal of Computational Physics. 2001,18(2):133-137 (In Chinese.))
[98]. J.-Ch. Robinnet, J. Gressier, G. Casalis, J.-M. Moschetta. Shock Wave Instability and the Carbuncle Phenomenon: Same Intrinsic Origin? J. Fluid Mech. 2000,417:237-263
[99]. M. S. Liou, Jr., C. J. Steffen. A New Flux Splitting Scheme. Journal of Computational Physics. 1993, 107:23-39
[100]. S. Aso, K. Hayashi, M. Mizoguchi. A Study on Aerodynamic Heating Reduction due to Opposing Jet in Hypersonic Flow. 40th AIAA Aerospace Sciences Meeting & Exhibit. AIAA 2002-0646. Reno, NV. January 14-17, 2002
[101]. Meng-Sing Liou, Pieter G. Buning. Contribution of The Recent AUSM Schemes to The Overflow Code: Implimentation and Validation. AIAA 2000-4404. 2000
[102]. Hirotaka Otsu, Akihiro Sasoh, Kazuhisa Fujita, Takashi Abe. Assessment of the Thermochemical Model for a Super-orbital Reentry Flow. 8(th) AIAA/ASME Joint Thermophysics and Heat Transfer Conference. AIAA 2002-3310. St. Louis, Missouri. June 24-26, 2002
[103]. M. Kaneko, I. Menshov. Y. Nakamura. Reflected Shock Wave/Boundary Layer Interaction in High-Enthalpy Shock Tunnel. AIAA 2000-2600. 2000
[104]. Yang-Yao Niu. Numerical Simulation of Dynamic Stall Using Upwind Methods and RNG Turbulence Models. AIAA 98-0419. 1998
[105]. Yang-Yao Niu. On Some Simple and Robust Riemann Solvers for Compressible Two-Phase Flows. 15th AIAA Computational Fluid Dynamics Conference. AIAA-2001-2647. Anaheim, CA. June 11-14, 2001
[106]. Munetsugu Kaneko, Igor Menshov, Yoshiaki Nakamura. Computation of Nozzle Starting Process with Thermal and Chemical Nonequilibrium in High-Enthalpy Shock Tunnel. 40(th) AIAA Aerospace Sciences Meeting & Exhibit. AIAA 2002-0142. Reno, NV. Jan 14-17, 2002
[107]. R. Agarwal, J. Augustinus. A Comparative Study of Advection Upwind Split (AUSM) and Wave/Particle Split (WPS) Schemes for Fluid and MHD Flows. 30th Plasmadynamics and Lasers Conference. AIAA 99-3613. Norfolk, VA. June 28-July 1, 1999
[108]．张涵信．无波动，无自由参数的耗散差分格式．空气动力学报，1988，6(1)
[109]. Shen Qing. Zhang Hanxin. A New Upwind NND Scheme for Euler Equations and Its Application to The Supersonic Flow. Proceedings of Asia Workshop on CFD. Sichuan, China. September 12, 1994
[110]. Joon Ho Lee, Oh Hyun Rho. Numerical Analysis of Hypersonic Viscous Flows Around a Blunt Body Using Roe's FDS and AUSM+ schemes. 28(th) AIAA Fluid Dynamics Conference and 4(th) AIAA Shear Flow Control Conference. AIAA Paper 97-2054. Snowmass Village, CO. June 29-July 2,1997
[111]. Joon Ho Lee, Oh Hyun Rho. Accuracy of AUSM+ Scheme in Hypersonic Blunt Body Flow Calculations. AIAA 98-1538.1998
[112]. K. H. Kim, O. H. Rho. An Improvement of AUSM Schemes by Introducing The Pressure-Based Weight Functions. The fifth Annual Conference of the Computational Fluid Dynamics Society of Canada (CFD 97). 1997: (14-33)-(14-38).
[113]. Kyu Hong Kim, Joon Ho Lee, Oh Hyun Rho. An Improvement of AUSM Schemes by Introducing The Pressure-Based Weight Functions. Computers & Fluids. 1998, 27(3):311-346
[114]. Kyu Hong KIM, Chongam KIM, Oh Hyun RHO. Accurate Computations of Hypersonic Flows Using AUSMPW+ Scheme and Shock-Aligned Grid Technique. AIAA 98-2442. 1998
[115]. Thomas. R. A. Bussing, Earll M. Murman. Finite-Volume Method for the Calculation of Compressible Chemically Reacting Flows. AIAA J. 1988,. 26(9): 1070-1078
[116]. Shigeru Aso, Takuji Kurotaki, Yoshiyuki Miyamoto. Experimental and Computational Study on Reduction of Aerodynamic Heating Load by Film Cooling in Hypersonic Flows. AIAA 97-0770. 1997
[117]. P. Stoll, P. Gerlinger, D. Br(?)ggemann. Domain Decomposition for an Implicit LU-SGS Scheme using Overlapping Grids. AIAA 97-1896. 1997
[118]．柳军．飞船返回舱三维化学非平衡流全流场数值模拟．国防科技大学研究生院硕士学位论文．2000年3月
[119]. Le Jia-ling, Wu Ying-chuan et al. Computational Interferometry for Three-Dimension Flow. Experiments and Measurements in Fluid Mechanics. 2001, 15(2)
[120]．卞荫贵，徐立功．气动热力学．合肥：中国科学技术大学出版社，1997：156
[121]. Luen T. Tam, Michael Y. An, Charles H. Campbell. Nonequilibrium Hypersonic Flow Computation for Weakly Ionized Air and Comparison with Flight Data, AIAA 24(th) Plasmadynamics & Lasers Conference. AIAA 93-3195. Orlando, FL. July 6-9, 1993
[122]．黄华，瞿章华．飞船轴对称热化学非平衡流场数值求解．国防科技大学学报．1999，21(3)：1-4 (Huang hua. Qu zhang-hua. Axial Symmetric Numerical Simulation of Thermochemical Nonequilibrium Flow over Spaceship. Journal of National University of Defense Technology. 1999, 21 (3):1-4 (In Chinese))
[123]．欧阳水吾，谢中强．近代空气动力学丛书：高温非平衡空气绕流．北京：国防工业出版社．2001
[124]．柳军，曾明，瞿章华．飞船再入舱三维化学非平衡流数值模拟。国防科技大学学报．1999，21(6)：9-12 (Liu Jun. Zeng Ming. Qu Zhang-hua. Numerical Simulation of Three Dimensional Chemical Nonequilibrium Flow over The Reentry Vehicle. Journal of National University of Defense Technology. 1999, 21(6):9-12 (In Chinese))
[125]．袁先旭．非定常流动数值模拟及飞行器动态特性分析研究．中国空气动力研究与发展中心博士学位论文．2002
[126]. Roger Peyret, Handbook of Computational Fluid Mechanics, Academic Press Limited, 1996
[127]. S. K. Saxena, K. Ravi, Some Aspects of High-Speed Blunt Body Flow Computations with Roe Scheme, AIAA Journal. 1995, Vol.33(6)
[128]．黎作武．含激波旋涡和化学非平衡反应的高超音速复杂流场的数值模拟．中国空气动力研究与发展中心博士学位论文．1995
[129]. D. B. Wilkinson. Hypersonic Shock Tunnel Tests of the .05 Scale Apollo Force Model. FS-8, Cornell Aeronautical Laboratory Report AA-1712-W-1 (Prime NASA Apollo Contract NAS 9-150), Buffalo, NY, Oct. 1962
[130]. B. Hassan, G. V. Candler, D. R. Olynick. The Effect of Thermo-Chemical Nonequilibrium on the Aerodynamics of Aero braking Vehicles. AIAA 92-2877. 1992
[131]．泽尔道维奇，莱依捷尔．力学名著译丛：激波和高温流体动力学现象物理学(上册)．北京，科学出版社，1980：115，353，265，274，277，302，308，336，338
[132]．章冠人．光子流体动力学理论基础．1996．55
[133]. George W. Sutton, Arthur Sherman. Engineering Magnetohydrodynamics. Me Graw-Hill Book Company, New York.
[134]. L. C. Hartung. Predicting Radiation Heat Transfer in Thermochemical Nonequilibriun Flow Fields. N95-11936. 1995
[135]. J. O. Arnold, D. M. Cooper, Chul Park. Line-by-Line Transport Calculations for Jupiter Entry Probes. AIAA 79-1082. 1979
[136]．吴国祯．分子振动光谱学基础．北京：化学工业出版社，1990
[137]．林美荣，张包铮．原子光谱学导论．北京：科学出版社，1990
[138]. J. O. Arnold, E. E. Whiting, G. C. Lyle. Line by Line Calculation of Spectra from Diatomic Molecules and Atoms Assuming A Voigt Line Profile, J. Quant. Spectrose. Radiant. Transfer. 1969, 9.775-798
[139]. Kovacs, Istvan. Rotational Structure in Spectra of Diatomic Molecules. Adam Hilger Ltd, London, 1969
[140]．[加]G．赫兹堡．分子光谱与分子结构：第一卷双原子分子光谱．王鼎昌译．北京：科学出版社，1983：14，68，110，152，159，163．
[141]. A. W. Ali Excitation and Ionization Crosections for Electron Beam and Microwave Energy Deposition in Air. Memorandum Report 4598, Naval Research Laboratory, Washington, D. C. Feb. 1982
[142]. S. Slinkers, A. W. Ali. Electron Excitation and Ionization Rate Coefficients for N2,O2,NO,N, and O. Memorandum Report 4756, Naval Research Laboratory, Washington, D. C. Feb. 1982
[143]. C. Park. Calculation of Nonequilibrium Radiation in AOTV Flight Regimes. AIAA 84-0306,1984
[144]．黄祖洽，丁鄂江．现代物理学丛书：输运理论．北京：科学出版社．1987
[145]. C. D. Engle, R. C. Farmer. Ablation and Radiation Coupled Viscous Hypersonic Shock Layer. NASA Grant NGR 19-001059, 1971
[146]．郭正．包含运动边界的多体非定常流场数值模拟方法研究．国防科技大学研究生院博士学位论文．2002
[147]. J. J. Bertin. Hypersonic Aerothermodynamics. AIAA, Washington DC. 1994
[148]．吴家驹译．科学图书大库：工程师用图表便览．台北市徐氏基金会．1978
[149]．瞿章华等．高超声速空气动力学．第二版．国防科技大学出版社，2001
[150]．黄华．耦合辐射的非平衡流场数值研究[学位论文][D]．湖南长沙：国防科技大学研究生院．1999(Huang Hua. Numerical Study of Nonequilibrium Flowfield Coupled with Radiation: [D]. Hunan Changsha: Graduate School of NUDT. 1999 (In Chinese)).
[151]．曹文祥．再入体尾流光辐射工程计算方法．CARDC技术报告．1984