检索结果-内蒙古大学图书馆

您好，读者！请登录

内蒙古大学图书馆

首页
概况
党建
资源
服务
科研支持
- 论文收录引用证明
- 科技查新
知识产权
档案馆
帮助

咨询与建议

建议与咨询留下您的常用邮箱和电话号码，以便我们向您反馈解决方案和替代方法

您的常用邮箱：*

您的手机号码：*

问题描述：

当前已输入0个字，您还可以输入200个字

全部搜索
期刊论文
图书
学位论文
标准
纸本馆藏
外文资源发现
数据库导航
超星发现

高级检索

时间限定

出版年份：

文献类型

图书期刊文献学位论文多媒体

馆藏选择

电子馆藏纸本馆藏

核心期刊

全部期刊 SCI 收录期刊 SSCI 收录期刊 EI 收录期刊 CSCD 收录期刊 CSSCI 收录期刊

语言

中文英文

文献类型

期刊文献图书学位论文标准纸本馆藏

帮助

文字说明：

T=题名（书名、题名），A=作者（责任者），K=主题词，P=出版物名称，PU=出版社名称，O=机构（作者单位、学位授予单位、专利申请人），L=中图分类号，C=学科分类号，U=全部字段，Y=年（出版发行年、学位年度、标准发布年）

检索规则说明：

AND代表“并且”；OR代表“或者”；NOT代表“不包含”；(注意必须大写,运算符两边需空一格)

检索范例：

范例一：(K=图书馆学 OR K=情报学) AND A=范并思 AND Y=1982-2016
范例二：P=计算机应用与软件 AND (U=C++ OR U=Basic) NOT K=Visual AND Y=2011-2016

分类表

所选分类

>> <<

限定检索结果

文献类型

259 篇 会议
8 篇 期刊文献

馆藏范围

267 篇 电子文献
0 种 纸本馆藏

日期分布

学科分类号

258 篇 工学
- 240 篇 力学（可授工学、理...
- 178 篇 航空宇航科学与技...
- 94 篇 控制科学与工程
- 75 篇 机械工程
- 73 篇 仪器科学与技术
- 71 篇 计算机科学与技术...
- 71 篇 软件工程
- 33 篇 动力工程及工程热...
- 26 篇 电气工程
- 22 篇 电子科学与技术（可...
- 21 篇 光学工程
- 17 篇 化学工程与技术
- 16 篇 土木工程
- 14 篇 交通运输工程
- 7 篇 建筑学
- 5 篇 船舶与海洋工程
- 4 篇 材料科学与工程（可...
- 4 篇 信息与通信工程
- 3 篇 安全科学与工程
166 篇 理学
- 115 篇 物理学
- 72 篇 数学
- 28 篇 大气科学
- 14 篇 化学
- 9 篇 统计学（可授理学、...
- 5 篇 系统科学
- 3 篇 地球物理学
8 篇 管理学
- 7 篇 管理科学与工程(可...
- 2 篇 工商管理
2 篇 法学
- 2 篇 社会学
1 篇 经济学
- 1 篇 应用经济学
1 篇 军事学

主题

18 篇 actuators
17 篇 boundary layers
15 篇 nasa
12 篇 wind tunnels
11 篇 computational fl...
10 篇 airfoils
9 篇 angle of attack
9 篇 flow control
7 篇 reynolds number
5 篇 navier stokes eq...
5 篇 vortex flow
5 篇 adaptive optics
5 篇 unsteady flow
5 篇 aerodynamics
4 篇 velocity measure...
4 篇 laminar flow
4 篇 wavefronts
4 篇 aberrations
3 篇 swept wings
3 篇 ducts

机构

30 篇 flow physics and...
28 篇 aiaa
19 篇 nasa langley res...
15 篇 nasa langley res...
14 篇 nasa langley res...
13 篇 nasa langley res...
12 篇 aiaa united stat...
11 篇 flow physics and...
9 篇 flow physics and...
8 篇 flow physics and...
8 篇 center for flow ...
7 篇 flow physics and...
7 篇 university of no...
6 篇 flow physics and...
6 篇 department of ae...
6 篇 nasa langley res...
5 篇 nasa langley res...
4 篇 center for flow ...
4 篇 nasa langley res...
4 篇 flow physics and...

作者

36 篇 jumper eric j.
27 篇 balakumar p.
25 篇 corke thomas c.
20 篇 jenkins luther n...
16 篇 king rudolph a.
15 篇 khorrami mehdi r...
15 篇 yao chung-sheng
15 篇 amitay michael
12 篇 lin john c.
12 篇 koklu mehti
12 篇 rennie r. mark
12 篇 owens lewis r.
11 篇 kegerise michael...
11 篇 neuhart dan h.
10 篇 chou amanda
10 篇 allan brian g.
9 篇 jones gregory s.
8 篇 choudhari meelan...
8 篇 seifert avi
8 篇 andino marlyn y.

语言

261 篇 英文
6 篇 其他

检索条件"机构=Center for Flow Physics and Control"

共 267 条记录，以下是1-10 订阅

全选清除本页清除全部题录导出标记到"检索档案"

详细简洁

排序：

flow control on a Finite Swept and Tapered Wing Experiencing Massive Separation

Flow Control on a Finite Swept and Tapered Wing Experiencing...

引用

AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2025

作者： Mahns, Evan Amitay, Michael Center for Flow Physics and Control Department of Mechanical Aeronautical and Nuclear Engineering Rensselaer Polytechnic Institute TroyNY12180 United States Center for Flow Physics and Control Rensselaer Polytechnic Institute TroyNY12180 United States

ISBN: (纸本)9781624107238

The effect of a steady or an unsteady jet on a finite span wing with AR = 2 at Rec = 600 and angle of attack α = 18° is demonstrated. The wing has a taper ratio λ ≈ 0.27 with an unswept leading edge and a trailing edge swept forward 30°, which creates an inverted ram’s horn vortex post stall. The effect of three different jet orifice shapes (circular, elliptical, and rectangular) on the flow field were explored. The elliptical orifice is found to be the least intrusive to the flow. Additionally, the streamwise location of the jet was explored, where the effect of either a steady jet or an unsteady jet at Cb= 1 and Cb = 2 were compared. Both jets significantly reduced the extent of separation where the unsteady jet was more effective. The jet located near the separation line reduced separation by creating a virtual wall, outboard of which the flow was separated and inboard of the virtual wall the flow was mostly attached. In contrast, the jet located further upstream reduced separation mainly outboard of its spanwise location. © 2025, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.

关键词： Orifices

来源：评论

学校读者我要写书评

暂无评论

Active Separation control at NASA Langley Research center: A Tribute to Avraham ‘Avi’ Seifert

Active Separation Control at NASA Langley Research Center: A...

引用

AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2025

作者： Pack Melton, La Tunia NASA Langley Research Center Flow Physics and Control Branch MS 170 HamptonVA United States

ISBN: (数字)9781624107238

ISBN: (纸本)9781624107238

The late Dr. Avraham ‘Avi’ Seifert was a National Research Council (NRC) research associate working on active separation control research from 1996 to 1999 at the NASA Langley Research center (LaRC). While at LaRC, he led pioneering active flow control (AFC) research on periodic excitation as a means of controlling turbulent boundary layer separation at flight Reynolds numbers. In this paper we pay tribute to Avi by reviewing his LaRC active flow control research that includes the four years he was an NRC research associate and the summers following during which he was a visiting researcher. © 2025, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.

关键词： NASA

来源：评论

学校读者我要写书评

暂无评论

Active flow control Enhanced Aileron of the High-Lift Common Research Model at TakeoffCondition

Active Flow Control Enhanced Aileron of the High-Lift Common...

引用

AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2025

作者： Andino, Marlyn Y. Melton, Latunia Pack Koklu, Mehti Hannon, Judith NASA Langley Research Center Flow Physics and Control Branch Mail Stop: 170 HamptonVA23681 United States

ISBN: (数字)9781624107238

ISBN: (纸本)9781624107238

An experimental investigation was conducted in the NASA Langley 14- by 22-Foot Subsonic Tunnel on the NASA 10% scale High-Lift Common Research Model (CRM-HL) to improve the high-lift aerodynamic performance of the takeoff configuration. Active flow control (AFC) was applied at the aileron hinge line to control flow separation at high aileron deflection angles (%a) to increase lift-to-drag ratio (R/J). Improvements in low speed R/J can increase vehicle payload and/or range resulting in a more efficient vehicle. Aileron deflection angles of 0, 7.5 16, and 25 were investigated. flow control was applied to the two largest aileron deflections, which are considered the high-lift (HL) improved takeoff configurations. A companion paper will discuss baseline flow characteristics of the CRM-HL at the three takeoff conditions: reference, nominal, and HL-improved. In this paper, we focus on the aerodynamic improvement obtained when AFC was applied to %a = 16 relative to the nominal configuration, %a = 7.5. Multiple flow control parameters, including actuator type, spacing, and intensity, were investigated to evaluate the efficiency of the actuation system. The different AFC configurations tested were assessed with tuft visualization, steady surface pressure data, and force and moment data. The results indicated that all actuation types and spacings examined led to an increase in lift across the range of angles of attack investigated. flow separation was mitigated with the injection of momentum at the aileron hinge line. The configurations with the smallest spacing produced the highest improvement in R/J. Steady jet actuation showed higher efficiency but similar aerodynamic performance when compared to the sweeping jet actuators. This work was performed in support of the NASA Advanced Air Transport Technology (AATT) Project. © 2025, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.

关键词： NASA

来源：评论

学校读者我要写书评

暂无评论

Effect of Static and Dynamic motions on Aerodynamic Loads and vortical structures on a Chined Forebody Delta Wing

Effect of Static and Dynamic motions on Aerodynamic Loads an...

引用

AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2025

作者： Remneff, Paul Amitay, Michael Center for Flow Physics and Control Department of Mechanical Aerospace and Nuclear Engineering Rensselaer Polytechnic Institute TroyNY12180 United States James L. Decker’45 Endowed Chair of Aerospace Engineering Director Center for Flow Physics and Control Rensselaer Polytechnic Institute TroyNY12180 United States

ISBN: (数字)9781624107238

ISBN: (纸本)9781624107238

The effect of static and dynamic pitch and roll on the aerodynamic loads and the flowfield on a tailless chined forebody delta wing model were explored experimentally at Rec̅ = 2.33×105. For the wing level case (no roll) the aerodynamic loads suggested vortex breakdown at α = 28°–30°. Introducing a roll angle decreased the overall lift and drag coefficients for α > 22° while an increase in side force was observed. Roll angles also introduced non-zero roll and yaw moments caused by asymmetry between the vortices. When dynamically pitching or rolling, a hysteresis was observed in the lift and drag forces. Stereo particle image velocimetry experiments showed how the motions influenced the strength and location of the vortices, and thus explained the hysteresis. © 2025, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.

关键词： Delta wing aircraft

来源：评论

学校读者我要写书评

暂无评论

Testing of High-Lift Common Research Model at Takeoff Configurations

Testing of High-Lift Common Research Model at Takeoff Config...

引用

AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2025

作者： Koklu, Mehti Hannon, Judith A. Melton, Latunia P. Andino, Marlyn Y. NASA Langley Research Center Flow Physics and Control Branch MS 170 HamptonVA23681 United States NASA Langley Research Center HamptonVA23681 United States

ISBN: (纸本)9781624107238

The 10% scale High-Lift Common Research Model (CRM-HL) was tested in the NASA Langley 14- by 22 Foot Subsonic Tunnel (14x22) in support of the NASA Advanced Air Transport Technology (AATT) Project. The main objective of the wind tunnel test was to improve the aerodynamic performance of a representative aircraft model during takeoff operations using localized active flow control (AFC). This approach involves the application of AFC concepts locally to a relatively small region;therefore, it has the potential to cause minimal architectural change to current aircraft configurations. In addition, the power requirements of localized AFC could be supplied with onboard air resources. Recent exploratory studies identified the aileron as a target area for improving lift-to-drag ratio using localized AFC concepts. The idea is to deflect the ailerons beyond their nominal deflection angles and use AFC to reduce flow separation that occurs at larger aileron deflections. Several AFC concepts with different configurations were evaluated with the goal of achieving high-lift performance improvement. The assessment of AFC configurations is reported in a companion paper. The focus of the current paper is to report the data relevant to the CRM-HL takeoff configurations and establish a reference case for localized AFC application. Three takeoff configurations —reference, nominal, and high-lift improved—are documented. These takeoff configurations are obtained by varying aileron deflection. Wind tunnel measurements including surface static pressures and force and moment data are presented. In addition, surface tuft flow visualization, mainly on the aileron, is provided to understand the flow characteristics developed over the aileron during takeoff. © 2025, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.

关键词： NASA

来源：评论

学校读者我要写书评

暂无评论

Transition Measurements on the SWiFT Model in the National Transonic Facility

Transition Measurements on the SWiFT Model in the National T...

引用

AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2025

作者： Eppink, Jenna L. Sadowski, Shelly Andino, Marlyn Chan, David Moran, Bryce Flow Physics and Control Branch NASA Langley Research Center MS 170 HamptonVA23681 United States Configuration Aerodynamics Branch NASA Langley Research Center MS 499 HamptonVA23681 United States Jacobs Technology Inc NASA Langley Research Center Mail Stop 267 HamptonVA23681 United States

ISBN: (数字)9781624107238

ISBN: (纸本)9781624107238

Boundary layer transition locations on the Swept Wing flow Test (SWiFT) Hybrid Wing Body model were measured in the National Transonic Facility (NTF) at the NASA Langley Research center using several different methods. These methods include sublimating chemical f low visualization for a limited number of low Reynolds number conditions, as well as mean static pressure and dynamic pressure measurements. Results are presented for a range of conditions in the NTF, demonstrating Mach and Reynolds number effects. The transition front locations obtained from the different techniques agree well. A variation of the static pressure transition detection method is described in which continuous angle of attack polars are performed. This approach enables detection of the transition front at more challenging (high Reynolds number) conditions than is possible with sparser data from pitch-pause angle-of-attack polars. The trip dot effectiveness is also verified using all of the available diagnostics. Additionally, low Reynolds number results are compared with those acquired on the same model at the Aircraft Research Association (ARA) facility, and these results show good agreement overall, suggesting similar freestream flow quality conditions of the two facilities. © 2025, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.

关键词： NASA

来源：评论

学校读者我要写书评

暂无评论

$\mathcal{H}_{\infty}$ Phase Locking control for Wave Induced Wake Mixing

$\mathcal{H}_{\infty}$ Phase Locking Control for Wave Induce...

引用

American control Conference (ACC)

作者： Daniel Van Den Berg Delphine De Tavernier Jan-Willem Van Wingerden Delft Center for Systems and Control Delft University of Technology Delft The Netherlands Department of Flow Physics and Technology Delft University of Technology Delft The Netherlands

ISBN: (数字)9798350382655

ISBN: (纸本)9798350382662

The dynamic induction control wake mixing strategy has the potential to increase the energy yield of floating wind farms. These floating turbines will be subjected to surface waves, caused by the wind, and swell. When dynamic induction control is applied in open-loop, the effect of second-order wave forces and dynamic induction control on the thrust force can be out-of-phase and have destructive interference. In this work, we propose a method to synchronize the dynamic induction control input to the effect of the second-order wave forces. This is achieved by formulating the synchronization problem within an $\mathcal{H}_{\infty}$ optimization framework and designing a controller that minimizes the difference between the effect of wave-induced thrust variation and thrust variation. Time domain simulations show that synchronization at a desired frequency can be achieved and that the overall performance of the dynamic induction control method can be enhanced.

关键词： Time-frequency analysis Technological innovation Surface waves Dynamics Force Wind farms Wind turbines

来源：评论

学校读者我要写书评

暂无评论

Experimental and computational investigation of laser beam propagation through a free shear layer

Experimental and computational investigation of laser beam p...

引用

Unconventional Imaging, Sensing, and Adaptive Optics 2023

作者： Wells, Jonathan Kalensky, Matthew Rennie, R. Mark Jumper, Eric J. Quantum and Applied Optics Naval Information Warfare Center Atlantic HanahanSC United States Integrated Engagement Systems Department Naval Surface Warfare Center Dahlgren Division DahlgrenVA United States Institute of Flow Physics and Control University of Notre Dame Notre DameIN United States

ISBN: (纸本)9781510666009

Experimental Shack–Hartmann Wavefront Sensor (SHWFS) measurements were collected and examined to further understand image-plane irradiance pattern behavior in the presence of potentially sharp thermodynamic gradients. An analysis of path-integrated phase and image-plane irradiance pattern spreading discovered regions within a weakly compressible shear layer where sharp gradients were previously not observed. This paper describes the analysis process and shows results which suggest that Shack-Hartmann wavefront sensors are not adequately resolving sharp thermodynamic gradients in aberrating flows. © 2023 SPIE.

关键词： Wind tunnels

来源：评论

学校读者我要写书评

暂无评论

Time-shifted cost function design for more efficient dynamic wind farm flow control*

Time-shifted cost function design for more efficient dynamic...

引用

control Technology and Applications (CCTA),

作者： Marcus Becker Dries Allaerts Jan-Willem van Wingerden Delft Center for Systems and Control Delft University of Technology CD Delft The Netherlands Department of Flow Physics and Technology Delft University of Technology HS Delft The Netherlands

ISBN: (数字)9798350370942

ISBN: (纸本)9798350370959

Dynamic wind farm flow control is the art and science to maximize the energy yield of large wind farms. In this paper we will address the problem of large time delays between control actions of the different turbines in the farm and the delayed impact on the downstream turbines. We propose and show how a time-shifted cost function approach can render the receding horizon optimization problem more efficient and can mitigate the unavoidable turn-pike effect. We further show how the resulting setup can be used to break the optimization problem apart into several smaller optimization tasks to reduce the computational load. We demonstrate that the proposed changes do allow an economic model predictive control strategy to engage into collaborative wind farm control for long term gains, while a more traditional cost function approach leads to greedy turbine behavior. As a result, we take a crucial step towards a mature implementation of dynamic model based wind farm flow control.

关键词： Economics Art Delay effects Collaboration Wind farms Cost function Robustness

来源：评论

学校读者我要写书评

暂无评论

Secondary flow within High Curvature Virtual Duct Fences on a Flat Plate

Secondary Flow within High Curvature Virtual Duct Fences on ...

引用

AIAA Aviation and Aeronautics Forum and Exposition, AIAA AVIATION Forum 2021

作者： Pawlowski, Barry T. Mark Rennie, R. Jumper, Eric J. Department of Aerospace and Mechanical Engineering Center for Flow Physics and Control University of Notre Dame Notre DameIN46545 United States

ISBN: (数字)9781624106101

ISBN: (纸本)9781624106101

The flow over a surface can be effectively controlled using vertical fences that expand or contract in the cross-stream direction to slow or accelerate the flow as required. This passive flow-control approach, called the "virtual duct" was originally developed to mitigate aero-optical flows over hemispherical beam directors, but can also be applied to control the flow over any shaped surface. flow-visualization and other studies show, however, that streamwise vortices develop in the vicinity of the corners of the virtual-duct fences;these secondary flows and their effect on the duct performance are not well understood. This paper describes an experimental investigation into the secondary flows produced by the virtual-duct flow-control approach, for the simplified case of a virtual duct mounted on a flat plate. © 2021, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.

关键词： Ducts

来源：评论

学校读者我要写书评

暂无评论

没有更多数据了...

全选清除本页清除全部题录导出标记到“检索档案”

共27页 << < 1 2 3 4 5 6 7 8 9 10 > >>

检索报告对象比较合并检索0

隐藏清空

合并搜索

回到顶部

执行限定条件

内容：

评分：

请选择保存的检索档案：

请选择收藏分类：

订阅名称：

通借通还

温馨提示：

图书名称：

借书校区：

取书校区：

手机号码：

邮箱地址：

一卡通帐号：

电话和邮箱必须正确填写，我们会与您联系确认。

联系人：

所在院系：

联系邮箱：

联系电话：

内蒙古自治区呼和浩特市赛罕区大学西街235号邮编: 010021

建议与咨询 留下您的常用邮箱和电话号码，以便我们向您反馈解决方案和替代方法

时间限定

文献类型

馆藏选择

核心期刊

语言

文献类型

帮助

文字说明：

检索规则说明：

检索范例：

分类表

所选分类

限定检索结果

文献类型

馆藏范围

日期分布

学科分类号

主题

机构

作者

语言

请选择保存的检索档案： 新增检索档案 确定 取消

请选择收藏分类： 新增自定义分类 确定 取消

通借通还

建议与咨询留下您的常用邮箱和电话号码，以便我们向您反馈解决方案和替代方法

请选择保存的检索档案：

请选择收藏分类：