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Science China(Technological Sciences) 2013年第5期56卷 1055-1065页

作者： CHEN ZhenLi HAO LinZhao zhang binqian School of Aeronautics Northwestern Polytechnical University

In order to simulate the flow control problem by using Nanosecond Pulsed Dielectric Barrier Discharge(NSDBD),a one-zone inhomogeneous phenomenological model is constructed based on the experimental and theoretical *** model is coupled with the unsteady Navier-Stokes equations,which can well predict the compression-expansion wave structures and wave speed compared with experimental results and can be applied to the simulation of the flow control by using *** model is adopted to investigate the separation control over NACA0015 airfoil using the NSDBD plasma *** separation-control mechanisms are revealed that the spanwise vortices produced by the plasma actuation play the key *** plasma actuation can produce a spanwise vortex around the separation point near the leading *** spanwise vortices make the separated free-shear layer unstable and shed away,move downstream along the upper wall,control the flow near the wall,and bring outer flow with high kinetic energy into the near wall region to realize the effective separation control over the upper surface of the airfoil.

关键词： plasma Nanosecond Pulsed Dielectric Barrier Discharge (NSDBD) flow control flow separation numerical simulation

Aerodynamic Design Methodology for Blended Wing Body Transport

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Chinese Journal of Aeronautics 2012年第4期25卷 508-516页

作者： LI Peifeng zhang binqian CHEN Yingchun YUAN Changsheng LIN Yu College of Aeronautics Northwestern Polytechnical University Xi 'an 710072 China Shanghai Aircraft Design and Research lnstitute Commercial Aircraft Corporation of China Ltd. Shanghai200232 China

This paper puts forward a design idea for blended wing body（BWB）.The idea is described as that cruise point,maximum lift to drag point and pitch trim point are in the same flight *** to this design idea,design objectives and constraints are *** applying low and high fidelity aerodynamic analysis tools,BWB aerodynamic design methodology is established by the combination of optimization design and inverse design *** lift to drag ratio,pitch trim and acceptable buffet margin can be achieved by this design *** 300-passenger BWB configuration based on static stability design,as compared with initial configuration,the maximum lift to drag ratio and pitch trim are achieved at cruise condition,zero lift pitching moment is positive,and buffet characteristics is *** burn of 300-passenger BWB configuration is also significantly reduced as compared with conventional civil *** aerodynamic design is carried out under the constraints of BWB design requirements,the design configuration fulfills the demands for interior layout and provides a solid foundation for continuous work.

关键词： blended wing body aerodynamic configurations computational fluid dynamics optimization design inverse design

Assessment on critical technologies for conceptual design of blended-wing-body civil aircraft

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Chinese Journal of Aeronautics 2019年第8期32卷 1797-1827,1794页

作者： Zhenli CHEN Minghui zhang Yingchun CHEN Weimin SANG Zhaoguang TAN Dong LI binqian zhang School of Aeronautics Northwestern Polytechnical UniversityXi’an 710072China Shanghai Aircraft Design and Research Institute Commercial Aircraft Corporation of China LtdShanghai 201210China

Civil aviation faces great challenges because of its robust projected future growth and potential adverse environmental effects. The classical Tube-And-Wing(TAW) configuration following the Cayley’s design principles has been optimized to the architecture’s limit, which can hardly satisfy the further requirements on green aviation. By past decades’ investigations the BlendedWing-Body(BWB) concept has emerged as a potential solution, which can simultaneously fulfill metrics of noise, emission and fuel burn. The purpose of the present work is to analyze the developments of critical technologies for BWB conceptual design from a historical perspective of technology progress. It was found that the high aerodynamic efficiency of BWB aircraft can be well scaled by the mean aerodynamic chord and wetted aspect ratio, and should be realized with the trade-offs among stability and control and low-speed performance. The structure concepts of non-cylinder pressurized cabin are of high risks on weight prediction and weight penalty. A static stability criterion is recommended and further clear and adequate criteria are required by the evaluations of flying and handling qualities. The difficulties of propulsion and airframe integration are analyzed. The energy to revenue work ratios of well-developed BWB configurations are compared,which are 31.5% and 40% better than that of TAW, using state-of-art engine technology and future engine technology, respectively. Finally, further study aspects are advocated.

关键词： Aerodynamic design Bended-wing-body Propulsion Airframe Integration Stability and control Structure

Effects of stability margin and thrust specific fuel consumption constrains on multi-disciplinary optimization for blended-wing-body design

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Chinese Journal of Aeronautics 2019年第8期32卷 1847-1859页

作者： Minghui zhang Zhenli CHEN Zhaoguang TAN Wenting GU Dong LI Changsheng YUAN binqian zhang School of Aeronautics Northwestern Polytechnical UniversityXi’an 710072China Shanghai Aircraft Design and Research Institute Commercial Aircraft Corporation of ChinaLtd.Shanghai 200232China

Blended-Wing-Body(BWB) configuration, as an innovative transport concept, has become a worldwide research focus in the field of civil transports development. Relative to the conventional Tube-And-Wing(TAW) configuration, the BWB shows integrated benefits and serves as a most promising candidate for future ‘‘green aviation'. The objective of the present work is to figure out the effects of the stability margin and Thrust Specific Fuel Consumption(TSFC) on the BWB design in the framework of Multi-Disciplinary Optimization(MDO). A physically-based platform was promoted to study the effect static stability margin and engine technology level. Low-order physically based models are applied to the evaluation of the weight and the aerodynamic performance. The modules and methods are illustrated in detail, and the validation of the methods shows feasibility and confidence for the conceptual design of BWB aircrafts. In order to find out the relation between planform changes and the selection of stability and engine technology level, two sets of optimizations are conducted separately. The study proves that these two factors have dominant effects towards the optimized BWB designs in both aerodynamic shapes, weight distribution, which needs to be considered during the MDO design process. A balance diagram analysis is applied to find out a reasonable static stability margin range. It can be concluded that a recommended stability margin of a practical BWB commercial aircraft can be half of that of a conventional TAW design.

关键词： Aerodynamic design Blended-wing-body Multi-disciplinary optimization Optimization design Thrust specific fuel consumption

Nacelle-airframe integration design method for blended-wing-body transport with podded engines

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Chinese Journal of Aeronautics 2019年第8期32卷 1860-1868页

作者： Zhenqing XIN Zhenli CHEN Wenting GU Gang WANG Zhaoguang TAN Dong LI binqian zhang School of Aeronautics Northwestern Polytechnical UniversityXi’an 710072China Shanghai Aircraft Design and Research Institute Commercial Aircraft Corporation of ChinaLtd.Shanghai 200232China

Strong shock waves and flow separation often occur during the integration of nacelle and airframe for blended-wing-bodies with podded engines. To address this problem, this paper presents an integration method with numerical simulations. The philosophy of channeling flow and avoiding the throat effect on the nacelle and airframe is established based on the analysis of flow interference in the initial configuration. A parametric integration design method is proposed from twodimensional plane to three-dimensional space with control mechanisms and selection principles of the key parameters determined by their influences. Results show that strong shock waves and flow separation can be successfully eliminated under the influence of both the reshaped channel and decelerated inflow below the nacelle. Supersonic regions around the nacelle are effectively reduced, concentrating mainly on the lip position. Thus, a significant cruise drag reduction(8.7%) is achieved though the pressure drag of the nacelle increases.

关键词： Blended-wing-body Computational fluid dynamics Drag reduction Flow interference Nacelle-airframe integration

Investigation of micro vortex generators on controlling flow separation over SCCH high-lift configuration

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Science China(Technological Sciences) 2012年第8期55卷 1943-1953页

作者： CHU HuBing zhang binqian CHEN YingChun LI YaLin MAO Jun School of Aeronautics Northwestern Polytechnical UniversityXi'an 710072China Commercial Aircraft Corporation of China Ltd Shanghai Aircraft Design and Research InstituteShanghai 200235China

For the problem that the flow separation on the flap lowers the aerodynamic performance of high lift system,an investigation was carried out on using micro vortex generators(VGs) to control the separation on flap of the swept constant chord half-model(SCCH) high-lift configuration,at a small to medium angle of attack,by experimental and numerical *** basic flow characteristics of SCCH landing configuration were analyzed by using numerical method to provide required information for the design of micro ***,by keeping the cruise configuration intact,the preliminary design procedure and design methods of micro VGs were *** addition,the micro VGs were *** effects of VG's arrangement and geometric parameters,such as the arrangement mode,chordwise position,arrangement angle,height and spanwise distance,on controlling efficiency were investigated by using numerical *** the parameters of preliminary VGs were adjusted as the basis configuration for wind tunnel *** experiments were accomplished in NH-2 wind tunnel for validating the numerical method,as well as obtaining the design principles and methods of micro *** parameters of VGs were also optimized based on the *** experimental results showed that the numerical design method can serve as an efficient and accurate design *** lift and drag were increased by 10% and 14%,respectively in landing state,which satisfied the requirements for ***,it was concluded that the established design principles and methods for micro VGs in this investigation can be used in engineering application.

关键词： micro vortex generators high lift system flow control numerical simulation wind tunnel test

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基于改进直接曲率法的一种气动反设计方法研究

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西北工业大学学报 2011年第4期29卷 529-535页

作者：沈冬张彬乾陈迎春西北工业大学航空学院陕西西安710072 中国商用飞机有限责任公司上海飞机设计研究所上海200232

采用直接曲率法(DISC)反设计模块耦合NS方程流场求解程序,建立了具有跨声速翼型和机翼设计能力的气动设计平台。针对翼型表面光顺和跨声速设计中出现的收敛性问题,提出了基于最小二乘法原理的形状改变量曲线拟合方法,可显著改善跨声速... 详细信息

采用直接曲率法(DISC)反设计模块耦合NS方程流场求解程序,建立了具有跨声速翼型和机翼设计能力的气动设计平台。针对翼型表面光顺和跨声速设计中出现的收敛性问题,提出了基于最小二乘法原理的形状改变量曲线拟合方法,可显著改善跨声速设计收敛速度;提出的翼型前缘形状的多项式插值方法,可消除DISC方法中旋转变换而带来的翼型前缘不光顺问题,且具有加速收敛和增强设计稳定性的作用。

关键词：直接曲率法反设计曲线拟合多项式插值

无尾布局嵌入式舵面的大迎角纵向操纵能力研究

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航空学报 2012年第3期33卷 430-437页

作者：孙静张彬乾杨广珺西北工业大学航空学院陕西西安710072 西北工业大学无人机特种技术重点实验室陕西西安710065

针对某前掠翼翼身融合无尾布局由鸭面与尾舵组成的纵向基本控制舵面在大迎角状态操纵效率降低的问题,采用数值模拟方法研究一种机身下表面嵌入式新概念纵向操纵舵面实施大迎角纵向操纵补充的可行性。提出了嵌入式舵面的设计思想,研究了... 详细信息

针对某前掠翼翼身融合无尾布局由鸭面与尾舵组成的纵向基本控制舵面在大迎角状态操纵效率降低的问题,采用数值模拟方法研究一种机身下表面嵌入式新概念纵向操纵舵面实施大迎角纵向操纵补充的可行性。提出了嵌入式舵面的设计思想,研究了嵌入式舵面高度、偏度及其与尾舵组合时的相对位置等参数影响,提出了嵌入式舵面的设计原则、流动机理以及提供低头力矩增量的作用原理。研究结果表明:嵌入式舵面是无尾布局飞机大迎角纵向操纵的高效补充措施,单独使用,最大可提供约平衡10°迎角的低头操纵力矩,并对升阻特性影响很小;与尾舵组合使用,在研究迎角范围内(迎角α≤32°),可提供约6°迎角的低头平衡力矩增量,且对升阻性能产生有利影响。本文工作可为其他翼身融合无尾布局的气动舵面设计提供借鉴。

关键词：无尾布局嵌入式舵面尾舵大迎角纵向操纵

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前掠翼气动特性研究

西北工业大学学报 1989年第3期7卷 321-328页

作者：张彬乾 B.Laschka 西北工业大学联邦德国布伦瑞克工业大学

为适应飞机新布局发展的需要,进行了前掠翼空气动力特性的低速实验研究。研究内容包括:单独机翼和翼身组合体的纵横向气动特性、流谱及旋涡特性。研究结果表明:前掠翼具有良好的升阻特性,力矩特性及失速特性,可以提供较大的可用升力和... 详细信息

为适应飞机新布局发展的需要,进行了前掠翼空气动力特性的低速实验研究。研究内容包括:单独机翼和翼身组合体的纵横向气动特性、流谱及旋涡特性。研究结果表明:前掠翼具有良好的升阻特性,力矩特性及失速特性,可以提供较大的可用升力和良好的大迎角大侧滑角机动性。以上优点在翼身组合体上更为明显。实验发现前掠翼后缘出现后缘涡,观察了前掠翼特有的前后缘涡系的发生和发展,分析了产生前后缘涡系的原因及前后缘涡系对气动特性的影响。

关键词：前掠翼气动特性流态旋涡

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W型无尾布局复合式气动舵面设计研究

西北工业大学学报 2008年第6期26卷 698-702页

作者：王元元张彬乾沈冬西北工业大学航空学院陕西西安710072

文章针对W型无尾新概念布局的操纵控制问题,采用复合式气动舵面设计概念,提出了两段可动式侧板、副翼、襟翼、升降舵、方向舵、全动翼梢、阻力舵等气动舵面设计方案,通过风洞实验研究,获得了各舵面增升、纵向和横侧操纵效率,给出了各舵... 详细信息

文章针对W型无尾新概念布局的操纵控制问题,采用复合式气动舵面设计概念,提出了两段可动式侧板、副翼、襟翼、升降舵、方向舵、全动翼梢、阻力舵等气动舵面设计方案,通过风洞实验研究,获得了各舵面增升、纵向和横侧操纵效率,给出了各舵面的功能、不足及需解决的问题,提出了满足W型布局纵向和横侧操纵控制的舵面组合模式。研究结果也可供其它无尾布局飞机舵面设计参考。

关键词： W型布局复合式舵面风洞试验