76 resultados para boundary layer height
Receptivity to free-stream disturbance waves for blunt cone axial symmetry hypersonic boundary layer
Resumo:
Based on high-order compact upwind scheme, a high-order shock-fitting finite difference scheme is studied to simulate the generation of boundary layer disturbance waves due to free-stream waves. Both steady and unsteady flow solutions of the receptivity problem are obtained by resolving the full Navier-Stokes equations. The interactions of bow-shock and free-stream disturbance are researched. Direct numerical simulation (DNS) of receptivity to free-stream disturbances for blunt cone hypersonic boundary layers is performed.
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Effects of wall temperature on stabilities of hypersonic boundary layer over a 7-degree half-cone-angle blunt cone are studied by using both direct numerical simulation (DNS) and linear stability theory (LST) analysis. Four isothermal wall cases with Tw/T0= 0.5, 0.7, 0.8 and 0.9, as well as an adiabatic wall case are considered. Results of both DNS and LST indicate that wall temperature has significant effects on the growth of disturbance waves. Cooling the surface accelerates unstable Mack II mode waves and decelerates the first mode (Tollmien–Schlichting mode) waves. LST results show that growth rate of the most unstable Mack II mode waves for the cases of cold wall Tw/T0=0.5 and 0.7 are about 45% and 25% larger than that for the adiabatic wall, respectively. Numerical results show that surface cooling modifies the profiles of rdut/dyn and temperature in the boundary layers, and thus changes the stability haracteristic of the boundary layers, and then effects on the growth of unstable waves. The results of DNS indicate that the disturbances with the frequency range from about 119.4 to 179.1 kHz, including the most unstable Mack modes, produce strong mode competition in the downstream region from about 11 to 100 nose radii. And adiabatic wall enhances the amplitudes of disturbance according to the results of DNS, although the LST indicates that the growth rate of the disturbance of cold wall is larger. That because the growth of the disturbance does not only depend on the development of the second unstable mode.
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An approach which combines direct numerical simulation (DNS) with the Lighthill acoustic analogy theory is used to study the potential noise sources during the transition process of a Mach 2.25 flat plate boundary layer. The quadrupole sound sources due to the flow fluctuations and the dipole sound sources due to the fluctuating surface stress are obtained. Numerical results suggest that formation of the high shear layers leads to a dramatic amplification of amplitude of the fluctuating quadrupole sound sources. Compared with the quadrupole sound source, the energy of dipole sound source is concentrated in the relatively low frequency range.
Resumo:
The direct numerical simulation of boundary layer transition over a 5° half-cone-angle blunt cone is performed. The free-stream Mach number is 6 and the angle of attack is 1°. Random wall blow-and-suction perturbations are used to trigger the transition. Different from the authors’ previous work [Li et al., AIAA J. 46, 2899(2008)], the whole boundary layer flow over the cone is simulated (while in the author’s previous work, only two 45° regions around the leeward and the windward sections are simulated). The transition location on the cone surface is determined through the rapid increase in skin fraction coefficient (Cf). The transition line on the cone surface shows a nonmonotonic curve and the transition is delayed in the range of 0° ≤ θ ≤ 30° (θ = 0° is the leeward section). The mechanism of the delayed transition is studied by using joint frequency spectrum analysis and linear stability theory (LST). It is shown that the growth rates of unstable waves of the second mode are suppressed in the range of 20° ≤ θ ≤ 30°, which leads to the delayed transition location. Very low frequency waves VLFWs� are found in the time series recorded just before the transition location, and the periodic times of VLFWs are about one order larger than those of ordinary Mack second mode waves. Band-pass filter is used to analyze the low frequency waves, and they are deemed as the effect of large scale nonlinear perturbations triggered by LST waves when they are strong enough.The direct numerical simulation of boundary layer transition over a 5° half-cone-angle blunt cone is performed. The free-stream Mach number is 6 and the angle of attack is 1°. Random wall blow-and-suction perturbations are used to trigger the transition. Different from the authors’ previous work [ Li et al., AIAA J. 46, 2899 (2008) ], the whole boundary layer flow over the cone is simulated (while in the author’s previous work, only two 45° regions around the leeward and the windward sections are simulated). The transition location on the cone surface is determined through the rapid increase in skin fraction coefficient (Cf). The transition line on the cone surface shows a nonmonotonic curve and the transition is delayed in the range of 20° ≤ θ ≤ 30° (θ = 0° is the leeward section). The mechanism of the delayed transition is studied by using joint frequency spectrum analysis and linear stability theory (LST). It is shown that the growth rates of unstable waves of the second mode are suppressed in the range of 20° ≤ θ ≤ 30°, which leads to the delayed transition location. Very low frequency waves (VLFWs) are found in the time series recorded just before the transition location, and the periodic times of VLFWs are about one order larger than those of ordinary Mack second mode waves. Band-pass filter is used to analyze the low frequency waves, and they are deemed as the effect of large scale nonlinear perturbations triggered by LST waves when they are strong enough.
Resumo:
A direct numerical simulation of the shock/turbulent boundary layer interaction flow in a supersonic 24-degree compression ramp is conducted with the free stream Mach number 2.9. The blow-and-suction disturbance in the upstream wall boundary is used to trigger the transition. Both the mean wall pressure and the velocity profiles agree with those of the experimental data, which validates the simulation. The turbulent kinetic energy budget in the separation region is analyzed. Results show that the turbulent production term increases fast in the separation region, while the turbulent dissipation term reaches its peak in the near-wall region. The turbulent transport term contributes to the balance of the turbulent conduction and turbulent dissipation. Based on the analysis of instantaneous pressure in the downstream region of the mean shock and that in the separation bubble, the authors suggest that the low frequency oscillation of the shock is not caused by the upstream turbulent disturbance, but rather the instability of separation bubble.
Resumo:
A third-order weighted essentially nonoscillatory and non-free-parameter difference scheme magnetohydrodynamic solver has been established to investigate the mechanisms of magnetohydrodynamics controlling separation induced by an oblique shock wave impinging on a flat plate. The effects of magnetohydrodynamic interaction-zone location on the separation point, reattachment point, separation-bubble size, and boundary-layer velocity profiles are analyzed. The results show that there exists a best location for the magnetohydrodynamic zone to be applied, where the separation point is delayed the farthest, and the separation bubble is decreased up to about 50% in size compared to the case without magnetohydrodynamic control, which demonstrated the promising of magnetohydrodynamics suppressing the separation induced by shock-wave/boundary-layer interactions.
Resumo:
The particulate matter concentration above the seabed is usually assumed to decrease with height, following an exponential or Rouse profile. Many particulate matter concentration profiles with a peak were found on the North Mediterranean bottom water at a few tens of metres above the bottom. A particle size signal at the same altitude was found in this area and on the New York Eight shelf. It is assumed that this unexpected shape is due to a cloud of resuspended cohesive sediments originating from an impulse resuspension process. A simplified three-dimensional numerical model is proposed to describe the behaviour of resuspended particulate matter that originates from a sediment impulse vertically injected in the bottom water. This model reproduces the concentration profile shape observed, and it gives indications concerning the length and time characteristics of such a cloud, depending on the water velocity and bottom boundary layer properties.
Resumo:
The present paper investigates dispersed-phase flow structures of a dust cloud induced by a normal shock wave moving at a constant speed over a flat surface deposited with fine particles. In the shock-fitted coordinates, the general equations of dusty-gas
Resumo:
Supersonic combustion of thermally cracked kerosene was experimentally investigated in two model supersonic combustors with different entry cross-section areas. Effects of entry static pressure, entry Mach number, combustor entry geometry, and injection scheme on combustor performance were systematically investigated and discussed based on the measured static pressure distribution and specific thrust increment due to combustion. In addition, the methodology for characterizing flow rate and composition of cracked kerosene was detailed. Using a pulsed Schlieren system, the interaction of supercritical and cracked kerosene jet plumes with a Mach 2.5 crossflow was also visualized at different injection temperatures. The present experimental results suggest that the use of a higher combustor entry Mach number as well as a larger combustor duct height would suppress the boundary layer separation near the combustor entrance and avoid the problem of inlet un- start.
Resumo:
2 The flow of a compressible viscous fluid through a straight pipe.(可压缩黏性流体在直管中的流动1943年)
3 Two dimensional irrotational mixed subsonic and supersonic flow of a compressible fluid and the upper critical Mach number(可压缩流体二维无旋亚声速和超声速混合型流动及上临界马赫数1946年)
4 On the stability of transonic flows(论跨声速流的稳定性1947年)
5 The propagation of a spherical or a cylindrical wave of finite amplitude and the production of shock waves(有限振幅球面波或柱面波的传播及激波的产生1947年)
6 Two-dimensional irrotational transonic flows of a compressible fluid(可压缩流体二维无旋跨声速流动1948年)
7 On the hodograph method(关于速度图方法1949年)
8 Two-dimensional transonic flow past airfoils(绕翼型的二维跨声速流1951年)
9 On the stability of two-dimensional smooth transonic flows(论二元光滑跨声速流的稳定性1951年)
10 On the flow of an incompressible viscous fluid past a flat plate at moderate Reynolds numbers(中等雷诺数下不可压缩黏性流体绕平板的流动1953年)
11 Reflection of a weak shock wave from a boundary layer along a flat plate.I:Interaction of weak shock waves with laminar and turbulent boundary lavers analyzed by momentum-integral method(弱激波从沿平板的边界层的反射Ⅰ:用动量积分方法分析弱激波与层流和湍流边界层的相互作用1953年)
12 Reflection of weak shock wave from a boundary layer along a flat plate.Ⅱ:Interaction of oblique shock wave with a laminar boundary layer analyzed by differential-equation method(弱激波从沿平板的边界层的反射Ⅱ:用微分方程方法分析斜激波与层流边界层的相互作用1953年)
13 Plane subsonic and transonic potential flows(平面亚、跨音速势流1954年)
14 A similarity rule for the interaction between a conical field and a plane shock(锥型流和激波相互作用的相似律1955年)
15 Viscous flow along a flat plate moving at high supersonic speeds(沿高超声速运动平板的黏性流动【Ⅰ】1956年)
16 Viscous flow along a flat plate moving at high supersonic speeds(沿高超声速运动平板的黏性流动【Ⅱ】1956年)
17 The effects of Prandtl number on high-speed viscous flows over a flat plate(Prandtl数对绕平板高速黏性流的影响1956年)
18 Compressible viscous flow past a wedge moving at hypersonic speeds(楔的高超声速可压缩黏性绕流1956年)
19 Dissociation effects in hypersonic viscous flows(高超声速黏性流动中的离解效应1957年)
20 现代空气动力学的问题(1957年)
2l 在关于苏联发射成功第一颗人造卫星座谈会上的发言记录(1957年)
22 高超速钝体湍流传热问题(1963年)
23 宇宙飞船的回地问题(1965年)
24 激波的介绍
郭永怀生平
郭永怀传
Resumo:
height="210" align="left" />目录
- 访罗湖 忆当年[李佩]
- 怀念同窗益友郭永怀教授[钱伟长]
- 郭永怀追求科学、为国献身的一生[洪友士]
- 深深怀念为核盾牌献身的著名科学家--郭永怀先生 中国工程物理研究院
- 深切怀念郭永怀教授的奠基性贡献 中国空气动力研究与发展中心
- 胸怀长江长城 心系国家安危--纪念我国核防护工程奠基人郭永怀先生[周丰峻]
- 缅怀我们的首任系主任--郭永怀教授[辛厚文 马兴孝 俞书勤 何天敬]
- 科学和技术结合的典范--纪念郭永怀先生诞辰九十周年[郑哲敏 李家春]
- 怀念与感激[俞鸿儒]
- 继承先师遗愿,谈我所冲击动力学的发展--纪念郭永怀副院长诞辰九十周年[陈裕泽]
- 英名长存--纪念郭永怀副院长诞辰九十周年[沈中毅]
- 郭永怀与我国导弹弹头再入气动物理研究[魏叔如]
- 科研工作引路人--纪念郭永怀九十诞辰[胡在军]
- 科技楷模,引路良师--怀念敬爱的郭永怀副院长[朱竟洪 郑百瑛]
- 七律 永怀永怀郭老师[董务民]
- 留得春晖映核魂--怀念我们的好领导好老师郭永怀同志[孙德纶 张克才]
- 难以忘怀--忆郭永怀副院长事迹点滴[孙天雄]
- 研究工作与工程技术工作之间的关系[谈庆明]
- 忆敬爱的郭永怀老师[张兆顺 呼和敖德]
- 根深叶茂 厚积薄发--追忆恩师郭永怀先生教诲我打好基础[严宗毅]
- 力学前辈,科德风范[徐友钜]
- 领导的楷模 学者的典范 青年的导师--怀念郭永怀副院长[于长勤]
- 怀念郭永怀副院长[陈裕泽]
- 关于郭永怀事迹的回顾[张长富]
- 严谨的导师,可亲的长者--忆著名的空气动力学家郭永怀先生[吴兰春]
- 严谨细致 实事求是--纪念郭永怀九十诞辰[李启廉]
- 纪念核武器环境试验技术的奠基人--郭永怀副院长诞辰九十周年[李荣林]
- 郭老精神激励着材料科学研究的不断深入[周维宣 谭云]
- 郭永怀副院长的关怀与我所有机材料研究的发展[陈晓丽]
- 忆与郭永怀副院长的一次谈话[孙德纶]
- 缅怀郭永怀院士[陈家镛]
- 记郭永怀先生二三事[屠善澄]
- Remembering Yunghuai Kuo[C.C.Lin]
- Recall with love and respect[William R.Sears]
- Y.H.Kuo:An appreciation[Frank E.Marble]
- A commemorative tribute to Professor Guo Yonghuai[T.Y.Wu]
- Y.H.Kuo:A great scientist,revered teacher and good friend[Alfred Ritter]
- 氢氧燃烧及爆轰驱动激波管[俞鸿儒]
- 颗粒材料中致密波结构研究[孙锦山 朱建士 贾祥瑞]
- 网格与高精度差分计算问题[张涵信 呙超 宗文刚]
- 植被层湍流的大涡模拟[李家春 谢正桐]
- 半浮区液桥热毛细振荡流[唐泽眉 阿燕 胡文瑞]
- 再入湍流尾迹及其对雷达散射的影响研究[牛家玉 于明]
- 超声射流中CS2分子态分辨转动弛豫研究[陈从香 刘世林 戴静华 张志萍 马兴孝]
- 37mm冲压加速器实验和计算[柳森 简和祥 白智勇 平新红 部绍清]
- 化学体系中噪声诱导的时空有序结构和随机共振[辛厚文 侯中怀 杨灵法]
- 根据守恒律计算热流和摩阻的有限元提法[童秉纲 段占元]
- 高阶精度线性耗散紧致格式的渐近稳定性[邓小刚 毛枚良]
- 离散流体力学:理论和数值方法[高智]
- 2号复合离心机自动控制系统研制[王磊 林明 冯晓军]
- 海沧大桥气动弹性特性风洞试验研究[李明水 陈忻 张大康 王卫华]
- 内爆炸载荷下圆管变形、损伤和破坏规律的研究[李永池 李大红 魏志刚 孙宇新]
- 两种凝聚炸药的静态断裂性能实验研究[罗景润 韦日演 马丽莲]
- 圆柱体侵彻薄靶极限击穿速度估算探讨[吴应白 唐平]
- 动力学修改方法在夹具设计中的应用研究[蒲怀强 唐定勇]
- Numerical simulation of non-linear stability of two-dimensional supersonic boundary layer[Shen Qing Yuan Xiangjiang]
Resumo:
本书收录关于力学领域的论文301篇。内容包括:回顾20世纪力学在中国的发展,描绘了2000年中国和世界在力学各主要领域的发展现状;展望力学在21世纪的发展方向,探论新世纪中可能面临的新的重大力学等问题。
前言 | 白以龙;杨卫; | ||||||
力学学科《学科发展与优先领域战略研究报告》 | |||||||
世纪之交对力学的回顾、展望和想象 | 白以龙; | ||||||
计算流体力学中发展物理分析的几个问题 | 张涵信;李沁;宗文刚;张来平; | ||||||
非对称Riccati方程基于本征解的分析解 | 钟万勰; | ||||||
实验固体力学近几年的概况 | 伍小平; | ||||||
HIGHER-ORDER COHESIVE ELASTICITY THEORIES OF FRACTURE | Anna Vainchtein; | ||||||
疲劳短裂纹群体损伤随机特征研究 | 洪友士;郑亮;乔宇; | ||||||
半浮区热毛细对流及其不稳定性机理 | 胡文瑞;唐泽眉; | ||||||
ZONAL AND CORRELATION ANALYSIS IN SWEPT SHOCK/BOUNDARY LAYER INTERACTIONS | 邓学蓥; | ||||||
经典约束系统动力学的研究进展 | 梅凤翔; | ||||||
复杂系统的非线性动力学问题 | 陆启韶; | ||||||
时滞受控系统动力学研究进展 | 胡海岩;王在华; | ||||||
力学与航天器工程 | 马兴瑞;苟兴宇;周志成; | ||||||
采矿工程中的力学问题与分析 | 谢和平; | ||||||
CHALLENGING PROBLEMS IN FAILURE ANALYSIS OF DUAL-PHASE MATERIALS: CYCLIC MICRO-PLASTICITY AND SMALL FATIGUE CRACK TIP BEHAVIOR | |||||||
力学与国防科技 | 周丰峻; | ||||||
流体力学和气动热弹性力学新一代反命题的研究 | 刘高联; | ||||||
含灰气体近壁区流动及传热增强机制分析 | 王柏懿;戚隆溪;王超;江先金; | ||||||
三维定常、二维非定常分离模式及准则研究 | 吕志咏; |
Resumo:
height="150" align="left" />本文集收入了著名力学家、应用数学家、中国科学院院士谈镐生先生在流体力学、稀薄气体动力学和应用数学研究领域的论文和研究报告26篇,谈镐生先生倡导和支持力学基础研究的有关文章和论述21篇,谈先生的学术活动和生活图片多幅,以及谈镐生先生生平,最后附有谈先生生平年表。
目录
科技论文
Theaerodynamics of supersonic biplanes
Strength of reflected shock in Mach reflection
On laminar boundary layer over arotating blade
A unique law for ideal incompressible flow with preserved pattern off initeseparation
On motion of submerged cylinder
On source and vortex off luctuating strength U~aveling beneath a free surface
Wave sproduced by a pulsating source U~ave lingbeneath a free surface
On optimum nose Curves form issiles in the superaerodynamic regime
On optimum nose Curves for superaerodynamic missiles
On a special bolzavariational problem and the minimization of superaerodynamic
Hypersonic nose drag
Nose drag in free-molecule flow and its minimization
Final mdash;stagedecay of a single line vortex
Final stage decay of grid—produced turbulence
Resumo:
根据流动稳定性理论,将不稳定波的一个周期作为相干结构的初值,采用直接数值模拟方法对有压力梯度湍流边界层中相干结构的演化进行了研究,得出其各种特性的变化与实验凤测到的结果一致。
Resumo:
The turbulence structures near a sheared air-water interface were experimentally investigated with the hydrogen bubble visualization technique. Surface shear was imposed by an airflow over the water flow which was kept free from surface waves. Results show that the wind shear has the main influence on coherent structures under air-water interfaces. Low- and high- speed streaks form in the region close to the interface as a result of the imposed shear stress. When a certain airflow velocity is reached, "turbulent spots" appear randomly at low-speed streaks with some characteristics of hairpin vortices. At even higher shear rates, the flow near the interface is dominated primarily by intermittent bursting events. The coherent structures observed neat sheared air-water interfaces show qualitative similarities with those occurring in near-wall turbulence. However, a few distinctive phenomena were also observed, including the fluctuating thickness of the instantaneous boundary layer and vertical vortices in bursting processes, which appear to be associated with the characteristics of air-water interfaces.