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双语推荐：风洞

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风洞是风工程与空气动力学领域的重要实验装备。以浙江大学ZD-1边界层风洞的研制为背景,详细介绍了大型回流边界层风洞的技术参数确定、气动轮廓及立式结构设计方案、附属装置、动力控制系统、风洞维护方案、监控系统等内容,并对风洞建设与运行情况进行了说明。实践证明,大型回流边界层风洞的研制是成功的,可为今后类似风洞的研制提供参考。
The wind tunnel is an important experimental device in the field of wind engineering and aerodynamics . Taking the development of Zhejiang University ZD-1 boundary-layer wind tunnel as the background ,the technical requirement ,aerodynamic contour and vertical structure plan ,accessory facilities , power control system ,maintenance system and monitoring system of the large recirculating boundary-layer wind tunnel are introduced in detail .The wind tunnel construction process and operation situation are also described .Experience has proved that the development of a large recirculating boundary-layer wind tunnel is successful ,and it provides a reference for the design and construction of similar wind tunnels .

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本文归纳了风洞试验发展的历史背景，简述了美国AIAA风洞试验管理标准和从业者标准制定的过程和内容，重点阐述了标准中风洞试验的理念、管理和推荐的风洞试验具体做法，分析了标准中映射出的美国风洞试验技术的先进点，探讨了标准对改进国内风洞试验通常做法的启示。
This paper introduces the background of wind tunnel test development, summarizes the developing process and contents of the AIAA wind tunnel standards, expounds the thoughts, management method and the recommended practice of wind tunnel test project in standards, analyzes the advancements of American wind tunnel test techniques reflected from the standards, as well as discusses the inspirations from the usual practive of standards to improve domestic wind tunnel test.

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风洞试验段噪声(压力脉动)是评价风洞流场的重要指标之一,过强的噪声不但大大降低采集数据的精度和准度,同时会激起模型以及风洞部件的抖振响应,对材料造成严重的疲劳损伤,这一问题在跨声速风洞中犹为突出。本文从试验段噪声的成因展开论述,包括一般风洞中的共性问题和跨声速风洞中的个性问题;进而结合风洞实验对不同的试验段壁板型式、模型支架等的发声规律进行了探讨,并分析了各组分对风洞试验段总噪声水平的贡献。
The wind tunnel test section noise(pressure fluctuation)is one of the important indexes to evaluate the wind tunnel flow field,excessive noise not only significantly reducing the precision and accuracy of the collected data,but also arouses the model as well as wind tunnel parts buffeting response and causes serious fatigue damage to the materials,which is especially outstanding in transonic wind tunnels.This arti-cle discussed the causes of noise produced in the test section at first,with the common problems of general wind tunnels and the personalities of transonic wind tunnels included,and then based on wind tunnel tests studied sound laws of different test section wallboard type and model stand,analyzed the contribution for overall noise level from each component.

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风洞试验数据已广泛应用于航空航天飞行器、车辆、建筑、风力机等产品中。本文从风洞试验的技术层面出发,分析风洞试验数据生产过程中技术风险产生的根源,研究风洞试验数据不确定度的评定方法,提出了风洞试验数据技术风险的管控途径。
Wind tunnel test data has been widely applied in many national economic areas, such as aeronautical vehicles, cars, architectures, wind turbines etc. From the view of the technique point, this paper analyzed the reasons and process of technique risk during the wind tunnel data production, studied the assessment methods of the wind tunnel data uncertainty, presented the technique risk management and control methods for wind tunnel testing.

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本文主要介绍分析了美国卡尔斯潘公司的系列高超声速脉冲设备建设历程。为了适应不同的研究目的,卡尔斯潘公司先后建造了6座激波风洞和2座膨胀管风洞等脉冲设备,它们分别为11×15英寸激波风洞、48英寸激波风洞、96英寸激波风洞、无名高焓激波风洞、LENSⅠ激波风洞、LENSⅡ激波风洞、LENS X膨胀管风洞以及LENS XX膨胀管风洞。不管是设备规模,还是试验模拟能力以及测试技术水平,这些脉冲设备基本上代表了同期世界最高水平,并在一定时间内依然处于世界领先地位。本文通过对卡尔斯潘公司的LENS系列脉冲设备建设历程进行分析,希望可以对我国脉冲设备建设和发展相应的测试技术等提供一些有益的借鉴和参考。
This paper describes and analyses the serial hypersonic impulse facility building course of Calspan Corporation in USA.To meet the needs of different research,Calspan corpora-tion has built six shock tunnels and two expansion tunnels successively which include 1 1 ×1 5 inch shock tunnel,48 inch shock tunnel,96 inch shock tunnel,high enthalpy shock tunnel,LENS I shock tunnel,LENS II shock tunnel,LENS X expansion tunnel and LENS XX expansion tunnel. The dimension,simulation capability and testing technique all represent the tiptop level in the corresponding period.The analysis of LENS series impulse facility building course of Calspan Corporation would provide helpful information for building our national impulse facility and de-veloping test measurement tecnology.

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异形薄壁混凝土风洞工程主体结构复杂,施工难度大。基于实际工程,阐述了BIM在异形薄壁混凝土风洞工程施工阶段的应用,提供了风洞工程BIM施工模型的创建方法以及模型服务于具体施工过程的实践内容和路径,为BIM模型指导风洞工程施工打下基础。
The main structure of heterotypic thin?wall wind tunnel is complex and difficult to construct. This paper introduced the application of BIM in the construction stage for wind tunnel projects. The modeling method and experience of BIM model for wind tunnel are pointed out which is basement for BIM modeling application to guide construction of wind tunnel project.

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随着航空运输业的发展,先进飞行器的精细化设计要求有飞行雷诺数下的气动数据为支撑。大型低温高雷诺数风洞(如ETW、NTF)是真实再现飞行器飞行状态流动特性的最佳地面试验设备。文中归纳总结了大型高雷诺数风洞的实现途径和风洞型式,分析了当前低温风洞的国内外现状,深入剖析了大型连续式低温风洞设计建设的关键技术及解决措施,对我国自行开展大型低温高雷诺数风洞的设计建设具有重要参考意义,并对成功建设我国大型低温高雷诺数风洞进行了展望。
With the development of air transportations,detail-optimized designs of advanced aircrafts demand aerodynamic data under the flight Reynolds number conditions.Large-scale cry-ogenic wind tunnels,such as ETW and NTF,are the best ground testing facilities to obtain air-craft flow characteristics in the real flight conditions.To facilitate the development of large-scale high Reynolds number wind tunnels,the achieving means and types are summarized,the current developing status is discussed,the key technologies and solutions are analyzed in depth for design methodologies and construction concerns.Finally,the future designs and constructions of large-scale continuous cryogenic wind tunnel in China are prospected.

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对中国科学院新疆生态与地理研究所新建的可移动式环境风洞进行了流场测试,分析评价该风洞气动特性,期望对今后的风洞实验开展有所指导。本实验在室内进行,在空洞条件下,用皮托管测量不同风速下（7m.s-1,12m.s-1,16m.s-1）实验段截面风速分布沿流向的变化,测试内容包括风洞实验段的气流稳定性、横向均匀性、紊流度、边界层厚度的分布规律,并与其他环境风洞相比较。结果显示,该风洞气流稳定性系数小于1%,横向不均匀度小于2.5%,紊流度在1%左右,底板边界层和侧壁边界层分别为15cm和10cm,表明该风洞使用效果良好,设计合理。
Wind profiles and flow dynamic characteristics were investigated for a potable wind tunnel recently built by Xinjiang Institute of Ecology and Geography,Chinese Academy of Sciences.The objective of this research was to determine the suitability of the wind tunnel for experiment research and provide basic information for future experiments in this wind tunnel.The experiment was conducted in the empty wind tunnel condition.Wind profiles at ten heights under three wind speeds of 7,12,and 16 m·s-1 were measured with Pitot tubes.Five cross sections at 1-m distance in the experiment were investigated,and five wind speed profiles with 20-cm span were measured at each cross section.Results indicate that the flow stability coefficient is less than 1%,the transverse uniformity is less than 2.5%,the turbulence is about 1%,and the thickness of the bottom boundary layer and side wall boundary layer are 15 cm and 10 cm,respectively.This study suggests that this wind tunnel meets the desig

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为深入研究地面效应机理及地效翼空气动力特性，在同济大学上海地面交通工具风洞中心的空气动力-气动声学风洞内对地效翼模型进行了风洞试验。首先，根据地效翼空气动力特性及风洞试验能力，对风洞试验进行了设计；其次，在风洞试验中利用移动路面模拟系统和六分力天平测量系统，研究了地面粘性效应对地效翼空气动力的影响和地效翼空气动力特性。研究结果表明：固定地面附近边界层流动不仅与地效翼的高度有关，还与迎角有关；与移动地面相比，固定地面下测得的升力和阻力偏低，且由于固定地面边界层受气垫效应影响，失速延后。通过地效翼风洞试验研究揭示了移动路面模拟的重要性，并深入分析了地效翼空气动力特性，为地效飞行器空气动力设计和研究提供了参考。
A study on ground effect mechanism and aerodynamic characteristics of wing in ground effect was carried out in Aerodynamics/Aero-acoustic Wind Tunnel of Shanghai Automo-tive Wind Tunnel Center of Tongji University.Based on aerodynamics characteristics of the wing and the test ability of the wind tunnel,a wind tunnel test was firstly designed.Then an experi-mental study on ground viscous effect and aerodynamics was carried out by using moving belt system and six-component balance measurement system.It is shown that flow in boundary layer near the fixed ground is related not only to the distance between wing and ground,but also to the attack angle of this ground effect wing.The lift and the drag of the wing are lower while the stall angle is higher than that over a moving ground.Mechanism of ground effect was thoroughly in-vestigated,importance of moving ground simulation was discussed,and the aerodynamics of wing in ground effect was comprehensively analyzed through the experi

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本文概述美国NASA结冰研究发展历程，探讨美国以IRT结冰研究风洞为核心的结冰研究体系，研究我国结冰风洞未来的发展战略，建议以国家大型结冰风洞为平台，组建“结冰研究中心”，成立“中国结冰研究协会”，制订和发布“国家结冰研究规划”等。
This paper summarized the history of NASA icing research, analysed the icing research system about the IRT, researched the domestic icing wind tunnel development stratagem in future. The suggestions were given as follows: on the base of the national large icing wind tunnel, constructing an icing research center; China icing research association; drawing and releasing the national icing research program etc.

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