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苏霍伊设计局与美国联合设计和生产21世纪超声勤务喷气机
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作者 刘尚培 《低速气动力》 1991年第1期68-70,共3页
关键词 超声音速 喷气飞机 飞机
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二维超音速混合层增强混合的研究 被引量:10
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作者 曹 伟 周 恒 《中国科学(A辑)》 CSCD 北大核心 2002年第2期150-157,共8页
数值模拟了二维超音速混合层在入口处引入T-S波和在低速部分加入沿流向的振荡这两种不同的激励方式后流动的演化.结果表明,对于对流Mach数小于1的超音速混合层,两种方法均可增强混合,而加入振荡比引入T-S波更为有效.对加入振荡方式,还... 数值模拟了二维超音速混合层在入口处引入T-S波和在低速部分加入沿流向的振荡这两种不同的激励方式后流动的演化.结果表明,对于对流Mach数小于1的超音速混合层,两种方法均可增强混合,而加入振荡比引入T-S波更为有效.对加入振荡方式,还系统计算分析了各种参数对混合的影响。 展开更多
关键词 超声音速混合层 沿流向振荡 增强混合 混合装置
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Numerical Investigation of Particle Temperature Change in Supersonic Flows
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作者 Ryohei Sakamaki Masaya Suzuki Makoto Yamamoto 《Journal of Chemistry and Chemical Engineering》 2012年第9期825-831,共7页
Gas-particle two-phase flow is a very important consideration in designing various machines. Although a great deal of theoretical, experimental, and numerical research has been carried out, particle motion in a supers... Gas-particle two-phase flow is a very important consideration in designing various machines. Although a great deal of theoretical, experimental, and numerical research has been carried out, particle motion in a supersonic flow has not been sufficiently clarified. Hence, in order to clarify the interactions between flow and particles, the authors consider the characteristics of particle motion, especially at high temperatures. In the present study, the flow of a gas with a diluted particle load is to be simulated in a conventional converging-diverging supersonic nozzle. The turbulent gas flow in the nozzle is computed with the finite difference and RANS (raynolds averaged navier-stokes simulation) methods. The particle motion is simulated in a Lagrangian manner. In addition, taking into account the light particle loading, a weak coupling method is used. Through this investigation, it is shown that the particle velocity increases monotonically from the nozzle throat to the outlet. And it is shown that particles can be accelerated to higher velocities in helium than in nitrogen, and smaller particles tend to attain higher speed and lower static temperature. 展开更多
关键词 Gas-solid two-phase flow supersonic flow Euler-Lagrange coupling
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The measurement error analysis when a pitot probe is used in supersonic air flow 被引量:3
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作者 ZHANG XiWen HAO PengFei YAO ZhaoHui 《Science China(Physics,Mechanics & Astronomy)》 SCIE EI CAS 2011年第4期690-696,共7页
Pitot probes enable a simple and convenient way of measuring mean velocity in air flow. The contrastive numerical simulation between free supersonic airflow and pitot tube at different positions in supersonic air flow... Pitot probes enable a simple and convenient way of measuring mean velocity in air flow. The contrastive numerical simulation between free supersonic airflow and pitot tube at different positions in supersonic air flow was performed using Navier-Stokes equations, the ENN scheme with time-dependent boundary conditions (TDBC) and the Spalart-Allmaras turbulence model. The physical experimental results including pitot pressure and shadowgraph are also presented. Numerical results coincide with the experimental data. The flow characteristics of the pitot probe on the supersonic flow structure show that the measure- ment gives actually the total pressure behind the detached shock wave by using the pitot probe to measure the total pressure. The measurement result of the distribution of the total pressure can still represent the real free jet flow. The similar features of the intersection and reflection of shock waves can be identified. The difference between the measurement results and the actual ones is smaller than 10%. When the pitot probe is used to measure the region of L=0-4D, the measurement is smaller than the real one due to the increase of the shock wave strength. The difference becomes larger where the waves intersect. If the pitot probe is put at L=SD-10D, where the flow changes from supersonic to subsonic, the addition of the pitot probe turns the original supersonic flow region subsonic and causes bigger measurement errors. 展开更多
关键词 pitot probe supersonic air flow numerical simulation measurement error
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A rapid approach to convective aeroheating prediction of hypersonic vehicles 被引量:11
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作者 ZHAO JiSong GU LiangXian MA HongZhong 《Science China(Technological Sciences)》 SCIE EI CAS 2013年第8期2010-2024,共15页
A rapid approach to hypersonic aeroheating predictions in the stagnation region and downstream is developed in the present paper.The engineering method is used to calculate inviscid hypersonic flowfields to reduce tim... A rapid approach to hypersonic aeroheating predictions in the stagnation region and downstream is developed in the present paper.The engineering method is used to calculate inviscid hypersonic flowfields to reduce time cost,and a combination of the mass flow balance technique and the axisymmetric analog is proposed to account for the entropy swallowing effects.A three-dimensional linear method is derived to fit the vehicle surface flowfields.Then a new axisymmetric analog method based on linear flowfields and linear surface equations is developed,with the complexity and computational cost reduced dramatically.In the stagnation region,an implicit surface fitting is introduced to approximate the primary curvatures and a robust aeroheating prediction method is constructed.The proposed approach is verified on a variety of configurations including spherically blunted cone,double ellipsoid and aerospace vehicle.Numerical results indicate the followings:1)The approach predicts aeroheating in about one second and the results agree well with CFD simulations and wind-tunnel measurements;2)with the help of entropy correction,the precision is further improved in the streamline diverging regions on the vehicle surface,while little improvement is found after entropy correction in the regions where the streamlines do not diverge. 展开更多
关键词 aeroheating prediction linear flowfield axisymmetric analog three-dimensional stagnation point entropy swallowing
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Ignition, flame propagation and extinction in the supersonic mixing layer flow 被引量:7
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作者 ZHANG YunLong WANG Bing ZHANG HuiQiang 《Science China(Technological Sciences)》 SCIE EI CAS 2014年第11期2256-2264,共9页
The supersonic mixing layer flow,consisting of a relatively cold,slow diluted hydrogen stream and a hot,faster air stream,is numerically simulated with detailed transport properties and chemical reaction mechanisms.Th... The supersonic mixing layer flow,consisting of a relatively cold,slow diluted hydrogen stream and a hot,faster air stream,is numerically simulated with detailed transport properties and chemical reaction mechanisms.The evolution of the combustion process in the supersonic reacting mixing layer is observed and unsteady phenomena of ignition,flame propagation and extinction are successfully captured.The ignition usually takes place at the air stream side of braid regions between two vortexes due to much higher temperature of premixed gases.After ignition,the flame propagates towards two vortexes respectively located on the upstream and downstream of the ignition position.The apparent flame speed is 1569.97 m/s,which is much higher than the laminar flame speed,resulting from the effects of expansion,turbulence,vortex stretching and consecutive ignition.After the flame arrives at the former vortex,the flame propagates along the outer region of the vortex in two branches.Then the upper flame branch close to fuel streamside distinguishes gradually due to too fuel-riched premixed mixtures in the front of the flame and the strong cooling effect of the adjacent cool fuel flow,while the lower flame branch continues to propagate in the vortex. 展开更多
关键词 supersonic mixing layer IGNITION flame propagation EXTINCTION
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A high-efficiency aerothermoelastic analysis method 被引量:2
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作者 WAN ZhiQiang WANG YaoKun +1 位作者 LIU YunZhen YANG Chao 《Science China(Physics,Mechanics & Astronomy)》 SCIE EI CAS 2014年第6期1111-1118,共8页
In this paper,a high-efficiency aerothermoelastic analysis method based on unified hypersonic lifting surface theory is established.The method adopts a two-way coupling form that couples the structure,aerodynamic forc... In this paper,a high-efficiency aerothermoelastic analysis method based on unified hypersonic lifting surface theory is established.The method adopts a two-way coupling form that couples the structure,aerodynamic force,and aerodynamic thermo and heat conduction.The aerodynamic force is first calculated based on unified hypersonic lifting surface theory,and then the Eckert reference temperature method is used to solve the temperature field,where the transient heat conduction is solved using Fourier’s law,and the modal method is used for the aeroelastic correction.Finally,flutter is analyzed based on the p-k method.The aerothermoelastic behavior of a typical hypersonic low-aspect ratio wing is then analyzed,and the results indicate the following:(1)the combined effects of the aerodynamic load and thermal load both deform the wing,which would increase if the flexibility,size,and flight time of the hypersonic aircraft increase;(2)the effect of heat accumulation should be noted,and therefore,the trajectory parameters should be considered in the design of hypersonic flight vehicles to avoid hazardous conditions,such as flutter. 展开更多
关键词 aerothermoelastic two-way coupling unified hypersonic lifting surface theory piston theory FLUTTER
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Effects of the injector geometry on a sonic jet into a supersonic crossflow 被引量:3
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作者 WANG GuoLei CHEN LiWei LU XiYun 《Science China(Physics,Mechanics & Astronomy)》 SCIE EI CAS 2013年第2期366-377,共12页
Large-eddy simulation of a sonic injection from circular and elliptic injectors into a supersonic crossflow has been performed.The effects of injector geometry on various fundamental mechanisms dictating the intricate... Large-eddy simulation of a sonic injection from circular and elliptic injectors into a supersonic crossflow has been performed.The effects of injector geometry on various fundamental mechanisms dictating the intricate flow phenomena including shock/jet interaction,jet shear layer vortices and their evolution,jet penetration properties and the relevant turbulence behaviors have been studied systematically.As a jet issuing transversely into a supersonic crossflow,salient three-dimensional shock and vortical structures,such as bow,separation and barrel shocks,Mach disk,horseshoe vortex,jet shear layer vortices and vortex pairs,are induced.The shock structures exhibit considerable deformations in the circular injection,while their fluctuation becomes smaller in the elliptic injection.The jet shear layer vortices are generated at the jet periphery and their evolution characteristics are analyzed through tracing the centroid of these coherent structures.It is found that the jet from the elliptic injector spreads rapidly in the spanwise direction but suffers a reduction in the transverse penetration compared to the circular injection case.The turbulent fluctuations are amplified because of the jet/crossflow interaction.The vertical Reynolds normal stress is enhanced in the downstream of the jet because of the upwash velocity induced by the counter-rotating vortex pair. 展开更多
关键词 large-eddy simulation compressible turbulence supersonic flow JET shock wave shock and turbulence interaction
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DNS of a spatially evolving hypersonic turbulent boundary layer at Mach 8 被引量:6
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作者 LIANG Xian LI XinLiang 《Science China(Physics,Mechanics & Astronomy)》 SCIE EI CAS 2013年第7期1408-1418,共11页
This paper reports the direct numerical simulation (DNS) for hypersonic turbulent boundary layer over a flat-plate at Ma∞ =8 with the ratio of wall-to-freestream temperature equal to 1.9, which indicates an extremely... This paper reports the direct numerical simulation (DNS) for hypersonic turbulent boundary layer over a flat-plate at Ma∞ =8 with the ratio of wall-to-freestream temperature equal to 1.9, which indicates an extremely cold wall condition. It is primarily used to assess the wall temperature effects on the mean velocity profile, Walz equation, turbulent intensity, strong Reynolds analogy (SRA), and compressibility. The present high Mach number with cold wall condition induces strong compressibility effects. As a result, the Morkovin's hypothesis is not fully valid and so the classical SRA is also not fully consistent. However, some modified SRA is still valid at the far-wall region. It is also verified that the semi-local wall coordinate y* is better than conventional y+ in analysis of statistics features in turbulent boundary layer (TBL) in hypersonic flow. 展开更多
关键词 DNS compressibility effects turbulent boundary layer
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The Two-Dimensional Supersonic Flow and Mixing with a Perpendicular Injection in a Scramjet Combustor
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作者 Mohammad Ali S. Ahmed A.K.M. Sadrul Islam 《Journal of Thermal Science》 SCIE EI CAS CSCD 2003年第4期371-380,共10页
A numerical investigation has been performed on supersonic mixing of hydrogen with air in a Scramjet (Supersonic Combustion Ramjet) combustor and its flame holding capability by solving Two-Dimensional full Navier-Sto... A numerical investigation has been performed on supersonic mixing of hydrogen with air in a Scramjet (Supersonic Combustion Ramjet) combustor and its flame holding capability by solving Two-Dimensional full Navier-Stokes equations. The main flow is air entering through a finite width of inlet and gaseous hydrogen is injected perpendicularly from the side wall. An explicit Harten-Yee Non-MUSCL Modified-flux-type TVD scheme has been used to solve the system of equations, and a zero-equation algebraic turbulence model to calculate the eddy viscosity coefficient. In this study the enhancement of mixing and good flame holding capability of a supersonic combustor have been investigated by varying the distance of injector position from left boundary keeping constant the backward-facing step height and other calculation parameters. The results show that the configuration for small distance of injector position has high mixing efficiency but the upstream recirculation can not evolved properly which is an important factor for flame holding capability. On the other hand, the configuration for very long distance has lower mixing efficiency due to lower gradient of hydrogen mass concentration on the top of injector caused by the expansion of side jet in both upstream and downstream of injector. For moderate distance of injector position, large and elongated upstream recirculation can evolve which might be activated as a good flame holder. 展开更多
关键词 scramjet engine TVD scheme finite width of inlet supersonic mixing parallel air stream flame holding.
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Transition prediction of the supersonic boundary layer on a cone under the consideration of receptivity to slow acoustic waves 被引量:6
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作者 SU CaiHong ZHOU Heng 《Science China(Physics,Mechanics & Astronomy)》 SCIE EI CAS 2011年第10期1875-1882,共8页
Transition prediction of the supersonic boundary layer on a cone with small angle of attack and Mach number 3.5 is investi-gated under the consideration of receptivity to slow acoustic waves, as the acoustic waves are... Transition prediction of the supersonic boundary layer on a cone with small angle of attack and Mach number 3.5 is investi-gated under the consideration of receptivity to slow acoustic waves, as the acoustic waves are the main environmental distur-bances in a conventional, i.e. non-quiet, wind tunnel. It is shown that the e-N method can still yield fairly satisfactory results incomparison with those obtained in wind tunnel experiments, provided that the boundary layer receptivity to slow acousticwaves is properly taken into account, including the dependence of the amplitude of disturbances on the frequency andstream-wise location. Neither the conventional e-N method nor the improved e-N method can yield correct result of transitionprediction, because the receptivity mechanisms considered there are not in accord with the real situation in the wind tunnel. 展开更多
关键词 RECEPTIVITY boundary layer transition CONE e-N method
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Minimization of Classification Samples for Supercritical and Subcritical Patterns of Supersonic Inlet
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作者 CHANG Juntao ZHENG Risheng +5 位作者 YU Daren BAO Wen CHEN Fu JIANG Weiyu ZHU Shoumei ZHENG Riheng 《Journal of Thermal Science》 SCIE EI CAS CSCD 2014年第4期375-380,共6页
In order to investigate sample minimization for classification of supercritical and subcritical patterns in supersonic inlet, three optimization methods, namely, opposite one towards nearest method, closest one toward... In order to investigate sample minimization for classification of supercritical and subcritical patterns in supersonic inlet, three optimization methods, namely, opposite one towards nearest method, closest one towards the byper-plane method and random selection method, are proposed for investigation on minimization of classification samples for supercritical and subcritical patterns of supersonic inlet. The study has been carried out to analyze wind tunnel test data and to compare the classification accuracy based on those three methods with or without priori knowledge. Those three methods are different from each other by different selecting methods for samples. The results show that one of the optimization methods needs the minimization samples to get the highest classification accuracy without priori knowledge. Meanwhile, the number of minimization samples needed to get highest classification accuracy can be further reduced by introducing priori knowledge. Furthermore, it demonstrates that the best optimization method has been found by comparing all cases studied with or without introducing priori knowledge. This method can be applied to reduce the number of wind tunnel tests to obtain the inlet performance and to identify the supercritical/subcritical modes for supersonic inlet. 展开更多
关键词 Supersonic inlet Inlet supercritical/subcritical Sample minimization
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