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Study on the unified algorithm for three-dimensional complex problems covering various flow regimes using Boltzmann model equation

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Science china(Physics,Mechanics & Astronomy) 2009年第1期52卷 124-138页

作者： LI ZhiHui1,2 & ZHANG HanXin1 1 National Laboratory for Computational Fluid Dynamics, Beijing 100083, china 2 china aerodynamics research and development center, hypervelocity aerodynamics institute, mianyang 621000, china National Laboratory for Computational Fluid Dynamics Beijing China china aerodynamics research and development center Hypervelocity Aerodynamics Institute Mianyang China

The Boltzmann simplified velocity distribution function equation describing the gas transfer phenomena from various flow regimes will be explored and solved numerically in this study. The discrete velocity ordinate method of the gas kinetic theory is studied and applied to simulate the complex multi-scale flows. Based on the uncoupling technique on molecular movement and colliding in the DSMC method, the gas-kinetic finite difference scheme is constructed to directly solve the discrete velocity distribution functions by extending and applying the unsteady time-splitting method from computational fluid dynamics. The Gauss-type discrete velocity numerical quadrature technique for different Mach number flows is developed to evaluate the macroscopic flow parameters in the physical space. As a result, the gas-kinetic numerical algorithm is established to study the three-dimensional complex flows from rarefied transition to continuum regimes. The parallel strategy adapted to the gas-kinetic numerical algorithm is investigated by analyzing the inner parallel degree of the algorithm, and then the HPF parallel processing program is developed. To test the reliability of the present gas-kinetic numerical method, the three-dimensional complex flows around sphere and spacecraft shape with various Knudsen numbers are simulated by HPF parallel computing. The computational results are found in high resolution of the flow fields and good agreement with the theoretical and experimental data. The computing practice has confirmed that the present gas-kinetic algorithm probably provides a promising approach to resolve the hypersonic aerothermodynamic problems with the complete spectrum of flow regimes from the gas-kinetic point of view of solving the Boltzmann model equation.

关键词： Boltzmann model equation kinetic theory velocity distribution function discrete velocity ordinate technique hypersonic flow parallel computing numerical methods

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Numerical Simulation of Shock (Blast) Wave Interaction with Bodies

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Communications in Nonlinear Science and Numerical Simulation 1999年第1期4卷 1-7页

作者： Jialing LE (china aerodynamics research and development center P.O. Box 211 mianyang Sichuan china) china aerodynamics research and development center P.O. Box 211 mianyang Sichuan china China

Some typical results of computation on the shock (blast) wave interaction (2-D and 3-D) with bodies and its experimental validation in shock tube are summarized, suggestions for improving the numerical method (difference scheme and grid systems),developing 3-D optical quantitative visualization technology and further studying the unsteady turbulent flow are put forward.

关键词： shock wave blast wave numerical simulation

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Gas kinetic algorithm for flows in Poiseuille-like microchannels using Boltzmann model equation

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Science china(Physics,Mechanics & Astronomy) 2005年第4期48卷 496-512页

作者： LI Zhihui1,2, ZHANG Hanxin1 & FU Song2 ⒈ National Laboratory for CFD, hypervelocity aerodynamics institute,china aerodynamics research and development center,mianyang 621000,china 2.Department of Engineering Mechanics,Tsinghua University,Beijing 100084,china National Laboratory for CFD Hypervelocity Aerodynamics Institute China Aerodynamics Research and Development Center Mianyang China Department of Engineering Mechanics Tsinghua University Beijing China

The gas-kinetic unified algorithm using Boltzmann model equation have been extended and developed to solve the micro-scale gas flows in Poiseuille-like micro-channels from Micro-Electro-Mechanical Systems (MEMS). The numerical modeling of the gas kinetic boundary conditions suitable for micro-scale gas flows is presented. To test the present method, the classical Couette flows with various Knudsen numbers, the gas flows from short microchannels like plane Poiseuille and the pressure-driven gas flows in two-dimensional short microchannels have been simulated and compared with the approximate solutions of the Boltzmann equation, the related DSMC results, the modified N-S solutions with slip-flow boundary theory, the gas-kinetic BGK-Burnett solutions and the experimental data. The comparisons show that the present gas-kinetic numerical algorithm using the mesoscopic Boltzmann simplified velocity distribution function equation can effectively simulate and reveal the gas flows in microchannels. The numerical experience indicates that this method may be a powerful tool in the numerical simulation of micro-scale gas flows from MEMS.

关键词： Boltzmann model equation, discrete velocity ordinate method, finite-difference scheme, Couette flow, Poiseuille flow, gas flow in short-microchannel.

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TRANSONIC WALL IN TERFERENCE CORRECTIONS FOR CIVIL AIRCRAFT MODEL TESTS

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Chinese Journal of Aeronautics 1994年第3期7卷 160-169页

作者： Fan Zhaolin Cui Naiming Yun Qilin Yin Lupin(china aerodynamics research & development center,mianyang, Sichuan, china, 621000)

The correction method uses the static pressures measured near the tunnelwalls during model tests as boundary conditions. It is required that the flow near thewalls is subsonic and the freestream Mach number is less than 1. It is still valid whenthere are shock waves and supersonic pockets near the model as long as shock waves donot extend to walls, and the method is applicable to various ventilated wall or solid walltest sections. Corrections for three models tested abroad are in quite good agreementwith NASA's results, which are obtained by a nonhnear correction method. Thepresnet method has been apphed to B737 inodel tcsted in CARDC 1.2 m wind *** results show that this method is suitable for transonic wall interference correctionfor high aspect ratio airplane tests.

关键词： aerodynamic interference transonic wind tunnels wall pressure. data reduction

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MEASUREMENT OF TURBULENT BOUNDARY LAYER IN TRANSONIC FLOW

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Chinese Journal of Aeronautics 1993年第2期 79-84页

作者： Yun Qi-Iin,Zhao Chang-an (china aerodynamics research and development center,Sichuan,china,621000)

Hot-wire probes have been calibrated in FL-23 transonic and supersonic wind tunnelof CARDC （china aerodynamics research and development center）. The calibration resultshave shown that at a>0.6, the sensor sensitivity coefficient S almost does notchange with a; at a= 0.8 and Ma = 0.60～ 1.16, S almost does not vary with Machnumber. The mean flow and fluctuating flow characteristics within the boundary layer ofFL-23 wind tunnel’s test section side wall have been measured by the calibrated *** boundary layer mean flow characteristics measured by the hot wire are well in agreementwith those measured by Pitot tube. Fluctuating velocity and density （u’ / andp’ /） measured by the hot-wire within the boundary layer have shown that neither u’ / nor p’/ decreases monotonously with the increase of distance y from the tunnel wall.

关键词： DISA MEASUREMENT OF TURBULENT BOUNDARY LAYER IN TRANSONIC FLOW Flow

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Numerical simulations of leading-edge vortex core axial velocity for flow over delta wings

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Science china(Technological Sciences) 2009年第7期52卷 2029-2036页

作者： CHEN Lan1, 2 & WANG JinJun1 1 institute of Fluid Mechanics, Beijing University of Aeronautics and Astronautics, Beijing 100191, china 2 china Aerodynamic research and development center (CARDC), mianyang 621000, china institute of Fluid Mechanics Beijing University of Aeronautics and Astronautics Beijing China china Aerodynamic research and development center (CARDC) Mianyang China

Numerical simulations have been performed to investigate the characteristics of leading-edge vortex core axial velocity over two delta wings with leading edge swept angles Λ =50°and 76°, respectively. It is obtained that Reynolds number has the most important effect on the axial velocity of the primary leading-edge vortex core. At Reynolds numbers larger than 105, the jet-like flow of the vortex core is the most common type for both the large and the moderate swept delta wings. While if Reynolds number decreases to 103―104, the core axial velocity distributions for these two delta wings present the wake-like profile for all angles of attack considered in the present investigation.

关键词： delta wing low Reynolds number vortex flows

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Computations of Inlet/Isolator for SCRAMjet Engine

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Journal of Thermal Science 2000年第4期9卷 334-338页

作者： Wang Xiaodong,Le Jialing (china aerodynamics research & development center, R.O. Box 211, mianyang Sichuan, 621000, china )

The inlet/isolator is one of the important parts to the SCRAMjet engine. In the present paper, the flow fields within an inlet and isolator of a SCRAMjet engine have been simulated by the Reynolds-Averaged Navier-Stokes equations with the Baldwin-Lomax algebraic turbulence model. The second order H. C. Yee TVD scheme is used for the inviscid flux terms and a central difference considering the character of flow is used for the diffusion terms. The code was used to simulate the flow field of three types of the inlet/isolator models. The results show that the configuration of the internal compression surface of the inlet and the divergent angle of the isolator have a great important effect on the characteristics of the inlet/isolator.

关键词： inlet numerical simulation Navier-Stokes equations turbulence model.

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Numerical Simulation of Integrative Flow Field for Hypersonic Vehicle

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Journal of Thermal Science 2001年第2期10卷 103-108页

作者： HE Yuanyuan LE Jialing NI Hongli Computational Aerodynamic institute, china Aerodynamic research and development center, mianyang Sichuan 621000, china Computational Aerodynamic institute China Aerodynamic Research and Development Center Mianyang China

To meet the requirements for the aerodynamic performance and thrust force demanded in hypersonic missions, the integration design of fuselage and. engine must be considered for hypersonic vehicle with a scramjet engine. The configuration of wave rider is a typical hypersonic vehicle shape, whose fore-body can compress the flow in advance and provide uniform flow for the air intake, and whose aft-body,is used as an expansion surface of nozzle. In the present paper, an engineering method is applied to define total aerodynamic characteristics of an approximate wave rider configuration. A finite volume method based on the center of grid is also employed to numerically investigate the outflow pass the same configuration. The flow field details and the aerodynamic characteristics at given conditions are obtained. The evaluation for this configuration may be used as a guide for the hypersonic vehicle experiment.

关键词： hypersonic vehicle integration finite volume method.

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Quantitative measurement of hydroxyl radical(OH) concentration in premixed flat flame by combining laser-induced fluorescence and direct absorption spectroscopy

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Chinese Physics B 2016年第10期25卷 89-95页

作者：陈爽苏铁李中山白菡尘闫博杨富荣 Science and Technology on Scramjet Laboratory Hypervelocity Aerodynamics Institute of China Aerodynamic Research and Development Center china aerodynamics research and development center Division of Combustion Physics Lund University

An accurate and reasonable technique combining direct absorption spectroscopy and laser-induced fluorescence（LIF）methods is developed to quantitatively measure the concentrations of hydroxyl in CH;/air flat laminar flame. In our approach, particular attention is paid to the linear laser-induced fluorescence and absorption processes, and experimental details as well. Through measuring the temperature, LIF signal distribution and integrated absorption, spatially absolute OH concentrations profiles are successfully resolved. These experimental results are then compared with the numerical simulation. It is proved that the good quality of the results implies that this method is suitable for calibrating the OH-PLIF measurement in a practical combustor.

关键词： laser-induced fluorescence(LIF) direct absorption spectroscopy hydroxyl radical(OH) quantitative measurement

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The Continuous Dynamic Simulation Test of the Captive Trajectory System Used in 2.4m Transonic Wind Tunnel

The Continuous Dynamic Simulation Test of the Captive Trajec...

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2011 Chinese Control and Decision Conference（CCDC）

作者： Zhu Rusong is with the State Key Laboratory of aerodynamics,china aerodynamics research & development center,mianyang,621000,china. Wang Fei is with the State Key Laboratory of aerodynamics,china aerodynamics research & development center,mianyang,621000,china.Li Ping is with the china aerodynamics research & development center,mianyang,621000,china.Huang Xuhui is with the china aerodynamics research & development center,mianyang,621000,china.F

This paper presents the general process of velocity control of the Captive Trajectory Simulation System （CTS） used in 2.4m Transonic Wind Tunnel and it’s control *** two key technical problems in the velocity control of the CTS jig,including the continuous coordinated control of the jig along dynamic trajectory and the real-time filtering of the dynamic banlance signal,are disscussed in *** designing an optimized coordinated buffering control algorithm and two kinds of real-time filtering algorithms with little lag,the key technique problems are solved effectively and *** wind tunnel CTS test results shows that the simulating trajectory generated by the velocity control of the CTS jig is precisely identical as a whole to the test data generated by the move and stop control method,while the former test tecnique has greatly improved the efficiency of the CTS test in wind tunnel,and has reduced energy consumption considerably.

关键词： Captive Trajectory Simulation System Transonic Wind Tunnel Dynamic Trajectory Velocity Control Real-time Filtering

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