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Comparative study on aerodynamic heating under perfect and nonequilibrium hypersonic flows

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Science China(Physics,Mechanics & Astronomy) 2016年第2期59卷 78-84页

作者： Qiu Wang Jin Ping Li Wei Zhao Zong Lin Jiang State Key Laboratory of High Temperature Gas Dynamics Institute of Mechanics Chinese Academy of Sciences

In this study, comparative heat flux measurements for a sharp cone model were conducted by utilizing a high enthalpy shock tunnel JF-10 and a large-scale shock tunnel JF-12, responsible for providing nonequilibrium and perfect gas flows, respectively. Experiments were performed at the Key Laboratory of High Temperature Gas Dynamics(LHD), Institute of Mechanics, Chinese Academy of Sciences. Corresponding numerical simulations were also conducted in effort to better understand the phenomena accompanying in these experiments. By assessing the consistency and accuracy of all the data gathered during this study, a detailed comparison of sharp cone heat transfer under a totally different kind of freestream conditions was build and analyzed. One specific parameter, defined as the product of the Stanton number and the square root of the Reynold number, was found to be more characteristic for the aerodynamic heating phenomena encountered in hypersonic flight. Adequate use of said parameter practically eliminates the variability caused by the deferent flow conditions, regardless of whether the flow is in dissociation or the boundary condition is catalytic. Essentially, the parameter identified in this study reduces the amount of ground experimental data necessary and eases data extrapolation to flight.

关键词： aerodynamic heating hypersonic shock tunnel Stanton number sharp cone

CALCULATING METHOD OF aerodynamic heating FOR HYPERSONIC AIRCRAFTS

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Transactions of Nanjing University of Aeronautics and Astronautics 2013年第3期30卷 237-242页

作者：季卫栋王江峰 College of Aerospace Engineering Nanjing University of Aeronautics and Astronautics

A new calculating method of aerodynamic heating for unsteady hypersonic aircrafts with complex configuration is *** method,which considers the effects of high temperature chemical non-equilibrium and the heat transfer process in thermal protection structure,is based on the combination of the inviscid outerflow solution and the engineering method,where the Euler solver provides the flow parameters on boundary layer edge for engineering method in aerodynamic heating calculation.A high efficient interpolation technique,which can be applied to the fast computation of longtime aerodynamic heating for hypersonic aircraft,is developed for flying *** this paper,three hypersonic test cases are calculated,and the heat flux and temperature distribution of thermo-protection system are *** numerical results show the high efficiency of the developed method and the validation of thermal characteristics analysis on hypersonic aerodynamic heating.

关键词： hypersonic aircraft aerodynamic heating fluid-structure coupled analysis chemical non-equilibrium effects coupling of numerical and engineering methods

Effects of Wall Emissivity on aerodynamic heating in Scramjets

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Fluid Dynamics & Materials Processing 2020年第6期16卷 206-216页

作者： Yue Zhou Pengfei Ju School of Aeronautical Science and Technology Beihang UniversityBeijing100191China Tianjin Key Laboratory for Advanced Mechatronic System Design and Intelligent Control School of Mechanical EngineeringTianjin University of TechnologyTianjin300384China National Demonstration Center for Experimental Mechanical and Electrical Engineering Education(Tianjin University of Technology) Tianjin300384China

The effects of the wall emissivity on aerodynamic heating in a scramjet are *** supersonic turbulent combustion flow including radiation is solved in the framework of a decoupled strategy where the flow field is determined first and the radiation field *** particular,a finite difference method is used for solving the flow while a DOM(iscrete ordinates method)approach combined with a WSGGM(weighted sum of gray gases)model is implemented for radiative *** nonreactive turbulent channel flows are examined for a DLR hydrogen fueled scramjet changing parametrically the wall *** results indicate that the wall radiative heating rises greatly with increasing the wall *** the wall emissivity rises,the radiative source and total absorption increase,while the incident radiation decreases ***,although the radiative heating can reach a significant level,its contribution to the total aerodynamic heating is relatively limited.

关键词： Scramjet aerodynamic heating wall emissivity radiation

Numerical study on the influence of initial ambient temperature on the aerodynamic heating in the tube train system

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Advances in aerodynamics 2020年第1期2卷 579-596页

作者： Shijie Bao Xiao Hu Jukun Wang Tianhao Ma Yingyu Rao Zigang Deng School of Mechanics and Engineering Southwest Jiaotong UniversityChengdu 610031China State Key Laboratory of Traction Power Southwest Jiaotong UniversityChengdu 610031China

The evacuated tube transportation has great potential in the future because of its advantages of energy saving and environmental *** train runs in the closed tube at ultra-high *** heat quantity generated by aerodynamic heating is not easy to spread to external environment and then accumulates in the tube,inducing the ambient temperature in the tube to rise *** this paper,a three-dimensional geometric model and the Shear Stress Transport(SST)κ-ωturbulence model are used to study the influence of initial ambient temperature on the structure of the flow field in the *** results show that when the train runs at transonic speed,the supersonic flow region with low temperature and low-pressure is produced in the *** structure of the flow field of the wake will change with the initial ambient *** the higher the initial ambient temperature is,the shorter the low temperature region in the wake will *** larger temperature difference caused by the low temperature region may increase the temperature stress of the tube and affect the equipment inside the ***,the temperature inside the tube can be maintained at a reasonable value to reduce the influence of the low temperature region in the wake on the system.

关键词： Tube train Initial ambient temperature aerodynamic heating Numerical simulation

ILES of an array of three subsonic counter-flow jets issuing from a wing leading edge exposed to hypersonic aerodynamic heating

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Advances in aerodynamics 2020年第1期2卷 236-249页

作者： Tomonori Shimada Taku Ohwada Department of Aeronautics and Astronautics Graduate School of EngineeringKyoto UniversityKyoto 615-8530Japan

The flow of an active thermal protection system exploiting subsonic counter-flow jets for wing leading edges of hypersonic vehicles is numerically studied on the basis of the three dimensional Navier-Stokes *** coolant air issuing from around the stagnation point as an array of three jets spreads over both the upper and the lower sides of the cylinder surface and about 40~60%cooling effectiveness is achieved in the range up to 5 degrees angle of attack despite the occurrence of various three-dimensional fluid-dynamic *** numerical scheme is second order accurate but simple inclusion of high order polynomial approximation in the reconstruction enables the capturing of finer structure of the flow field.

关键词： Subsonic jet Counter-flow aerodynamic heating TPS Rayleigh-Taylor Kelvin-Helmholtz Near-wall streaks

Numerical Prediction of Flow Field and aerodynamic heating in the Gap of Hypersonic Vehicle

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Numerical Prediction of Flow Field and Aerodynamic Heating i...

Numerical analysis on the heat transfer of three types of nozzles for the hypersonic long-run wind tunnel

作者： Xue-wen SUN Hai-bo YANG Tao MI School of Mechanical Engineering University of Science and Technology Beijing Key Laboratory of Fluid Interaction with Material Ministry of Education Centre of Excellence for Advanced Materials School of Materials Engineering North China Institute of Aerospace Engineering

Prediction of flow field and thermal environment in the gap is crucial to the design of hypersonic vehicle thermal protection system. The compressible Navier-Stokes equation is solved to study the flow field and aerodynamic heating in the gap. The effect of inflow parameter on the aerodynamic heating is analyzed. The results show that there are vortex motions in the gap. The heat transfer in the gap mainly depends on the convection in the top region. The heat flux along the gap wall distributes in U-shape, and at the outlet of the gap is highest, which is the key point in the thermal protection design. As the angle of attack increases, the number of vortices will decrease gradually, and wall heat flux will increase, especially at the gap exit. The research results provide references for the design and optimization of thermal protection system.

关键词： Hypersonic Gap flow aerodynamic heating Numerical simulation

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Science China(Technological Sciences) 2015年第3期58卷 470-475页

作者： XING YunFei ZHONG FengQuan LI DongXia ZHANG XinYu National Key Laboratory of High Temperature Gas Dynamics Institute of Mechanics Chinese Academy of Sciences

The hypersonic long-run scramjet test tunnel is one of the key ground facilities for the studies of ramjet/scramjet and hypersonic thermal *** to the significantly large heat loading,the nozzle of the tunnel facility demands effective cooling *** this work,the two-dimensional,three-dimensional and axisymmetric Mach 6.5 nozzles at an inlet total temperature of 1840 K and a total pressure of 6.4 MPa were studied with main focuses on the properties of aerodynamic heating of *** present work aims to provide insights into the design of an effective cooling system for the nozzle and other components of the hypersonic long-run wind tunnel.

关键词： hypersonic scramjet test tunnel nozzle aerodynamic heating convective heat transfer

Transitional wave configurations between Type Ⅲ and Type Ⅳ oblique-shock/bow-shock interactions

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Chinese Journal of Aeronautics 2023年第3期36卷 96-106页

作者： Jun PENG Shuai LI Fan YANG Mingyue LIN Guilai HAN Zongmin HU State Key Laboratory of High-temperature Gas Dynamics Institute of MechanicsChinese Academy of SciencesBeijing 100190China The System Design Institute of Mechanical-Electrical Engineering Beijing 100854China School of Engineering Science University of Chinese Academy of SciencesBeijing 100049China

The interactions of oblique/bow shock waves are the key flow phenomena restricting the design and aerothermodynamic performance of high-speed *** Ⅲ and Type Ⅳ Shock/Shock Interactions(SSIs)have been extensively investigated,as such interactions can induce abnormal aerodynamic heating problems in hypersonic flows of *** transition process between these two distinct types of shock/shock interactions remains *** the present study,a subclass of shock/shock interaction configuration is revealed and defined as Type Ⅲ*** Ⅲa interaction can induce much more severe aerodynamic heating than a Type Ⅳ interaction which was ever reported to be the most serious in *** intense aerodynamic heating observed in this configuration highlights a new design point for the thermal protection system of hypersonic vehicles.A secondary Mach interaction between shock waves in the supersonic flow path of a Type Ⅲ configuration is demonstrated to be the primary mechanism for such a subclass of shock/shock interaction configuration.

关键词： Shock interactions Transitional configuration aerodynamic heating Shear layer Mach interaction

Investigation of thermal protection system by forward-facing cavity and opposing jet combinatorial configuration

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Chinese Journal of Aeronautics 2013年第2期26卷 287-293页

作者： Lu Haibo Liu Weiqiang Science and Technology on Scramjet Laboratory National University of Defense Technology Nanjing Artillery Academy

This paper focuses on the usage of the forward-facing cavity and opposing jet combinatorial configuration as the thermal protection system （TPS） for hypersonic vehicles. A hemispherecone nose-tip with the combinatorial configuration is investigated numerically in hypersonic free stream. Some numerical results are validated by experiments. The flow field parameters, aerodynamic force and surface heat flux distribution are obtained. The influence of the opposing jet stagnation pressure on cooling efficiency of the combinatorial TPS is discussed. The detailed numerical results show that the aerodynamic heating is reduced remarkably by the combinatorial system. The recirculation region plays a pivotal role for the reduction of heat flux. The larger the stagnation pressure of opposing jet is, the more the heating reduction is. This kind of combinatorial system is suitable to be the TPS for the high-speed vehicles which need long-range and long time flight.

关键词： aerodynamic heating Forward-facing cavity Hypersonic flow Opposing jet Thermal protection system