“W”型无尾布局飞机的气动外形研究
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摘要
本文研究了“W”型无尾布局的气动外形设计，阐述了该布局的气动设计思想，根据×××型无人机的总体设计技术指标，进行了气动外形设计，提出了两种气动布局方案：前掠翼无尾气动布局和“W”型无尾气动布局，利用UG建模软件和MGAERO气动分析计算软件计算了两种布局的纵、横向气动性能，分析了前掠翼前缘掠角和翼身融合对气动性能的影响，计算结果表明，“W”型气动布局的设计思想是正确的，所设计的“W”型无尾气动布局方案的气动性能优越，超过了总体设计技术指标。本文的工作体现在如下几点：
1．提出了具有自主知识产权的“W”型无尾气动布局的设计思想。
2．所设计的“W”型无尾气动布局的气动性能优越：
1)该布局具有优越的纵向气动性能，K_(max)=30；失速特性好，α=20°、C_1=1.9245，且未出现明显失速；纵向力矩呈现良好线性。
2)该布局滚转和偏航均不稳定，但力矩值都较小。
3．采用翼身全融合—升力体设计技术，不仅获得了优越的气动性能，而且也将对隐身性能带来好处，为总体布置和装载带来极大的灵活性。
4．分析了翼身融合设计参数的影响。
有关“W”型无尾气动布局的研究取得了初步的成果，但还有许多工作要做，需要进一步开展的工作主要有：
1．进一步完善布局设计，进行流动机理的深入研究；
2．进行布局操纵控制模式的研究；
3．研究解决无尾布局横航向稳定性的气动力措施。
This paper has mainly made a research on the aerodynamic configuration design of "W" tailless aircraft and the design idea has been presented here. According to the configuration design requirement of certain UAV, aerodynamic configuration design has been carried out and two configuration projects are given out at last: forward-swept wing tailless configuration and "W" tailless configuration. The longitudinal and lateral aerodynamic characteristics are obtained by using two aided soft: UG to build up geometrical models and MGAERO to calculate flow field. The investigation has been carried out the effects of sweep angle change and wing-fuselage fusion on the aerodynamic performance. The results indicate that the design idea of "W" aerodynamic configuration is right, the projects with this configuration has predominant aerodynamic characteristics which are greatly exceed the design demand.
The following work is performed:
1. The design idea of "W" tailless aerodynamic configuration has been presented which has independent knowledge property right.
2. The aerodynamic characteristics of "W" tailless configuration are excellent:
1) the project has excellent longitudinal aerodynamic, Kmax=30; good stall characteristic when a=20, C1=1 .9245, there is no sigh shows the stall and pitching moment is linear.
2) the project Has both rolling instability and yawing instability. But the moment value is small.
3. Taking use of wing-fuselage fusion lifting body design technology, which not only achieves good aerodynamic characteristic, but also is good to stealth and agility to system arrange.
4. The effects of wing-fuselage fusion design parameter have been analyzed. The investigation on "W" aerodynamic configuration has acquired primary
achievements, but there is still many work need to do. The further study is the folio wings:
1. To improve configuration design and put up flow mechanism investigation.
2. Carry through configuration control mode investigation.
3. To study the way to settle the yawing and rolling stability.
1．提出了具有自主知识产权的“W”型无尾气动布局的设计思想。
2．所设计的“W”型无尾气动布局的气动性能优越：
1)该布局具有优越的纵向气动性能，K_(max)=30；失速特性好，α=20°、C_1=1.9245，且未出现明显失速；纵向力矩呈现良好线性。
2)该布局滚转和偏航均不稳定，但力矩值都较小。
3．采用翼身全融合—升力体设计技术，不仅获得了优越的气动性能，而且也将对隐身性能带来好处，为总体布置和装载带来极大的灵活性。
4．分析了翼身融合设计参数的影响。
有关“W”型无尾气动布局的研究取得了初步的成果，但还有许多工作要做，需要进一步开展的工作主要有：
1．进一步完善布局设计，进行流动机理的深入研究；
2．进行布局操纵控制模式的研究；
3．研究解决无尾布局横航向稳定性的气动力措施。
This paper has mainly made a research on the aerodynamic configuration design of "W" tailless aircraft and the design idea has been presented here. According to the configuration design requirement of certain UAV, aerodynamic configuration design has been carried out and two configuration projects are given out at last: forward-swept wing tailless configuration and "W" tailless configuration. The longitudinal and lateral aerodynamic characteristics are obtained by using two aided soft: UG to build up geometrical models and MGAERO to calculate flow field. The investigation has been carried out the effects of sweep angle change and wing-fuselage fusion on the aerodynamic performance. The results indicate that the design idea of "W" aerodynamic configuration is right, the projects with this configuration has predominant aerodynamic characteristics which are greatly exceed the design demand.
The following work is performed:
1. The design idea of "W" tailless aerodynamic configuration has been presented which has independent knowledge property right.
2. The aerodynamic characteristics of "W" tailless configuration are excellent:
1) the project has excellent longitudinal aerodynamic, Kmax=30; good stall characteristic when a=20, C1=1 .9245, there is no sigh shows the stall and pitching moment is linear.
2) the project Has both rolling instability and yawing instability. But the moment value is small.
3. Taking use of wing-fuselage fusion lifting body design technology, which not only achieves good aerodynamic characteristic, but also is good to stealth and agility to system arrange.
4. The effects of wing-fuselage fusion design parameter have been analyzed. The investigation on "W" aerodynamic configuration has acquired primary
achievements, but there is still many work need to do. The further study is the folio wings:
1. To improve configuration design and put up flow mechanism investigation.
2. Carry through configuration control mode investigation.
3. To study the way to settle the yawing and rolling stability.
引文
[1] Epstein B., Luntz A. and Nachson A., Multigrid Euler Solver About Aircraft Configurations, with Cartesian Grids and Local Refinement, AIAA Paper 89-1960
[2] D.I.A. Poll and Cheng-Hao Qiu, Some effects of sweep direction and strakes for wings with sharp leading edges, The Aeronautical Journal, Volume 88 Number 878, October 1984.
[3] Zhang B Q, Yang Y N, An Investigation about Vertex Interference of the Canard Configuration at High Incidence. In: Proceedings of China-Japan Joint Symposium on Aerodynamics and Aircraft Design, Nanjing China, 1990, China Aviation Industry Press, 1990
[4] Mark A. Postdam, Blended Wing Body Analysis and Design, AIAA-97-2317
[5] Daniel G. Murri, Luat T. Nguyen, and Sue B. Grafton, Wind-Tunnel Free-Flight Investigation of a Model of a Forward-Swept-Wing Fighter Configuration, NASA Technical Paper 2230, 1984
[6] Takeshi OHNUKI and Nobuhiko KAMIYA, Transonic Investigations on High Aspect Ratio Forward- and Aft-Swept Wings, ICAS-88-2.2.1
[7] Spacht G, Bethpage, X-29:Managing an Integrated Advanced Technology Design, AIAA-86-2630
[8] D. Strohmever, W. Heinze, C. sterheld, L. Fornasier, Three Surface Aircraft - A Concept for Future Transport Aircraft, AIAA-00-0566
[9] J. H. McMasters, R. M. Cummings, Airplane Design - Past, Present and Future [Invited Paper], AIAA 2001-0535
[10] Barbara Pralio, Germana Vinelli, Giorgio Guglieri, Fulvia Quagliotti, Politecnico di Torino, Preliminary Design of a UAV Configuration, AIAA-2001-2422
[11] Rowena L. Eberhardi, David G. Ward, Indirect Adaptive Flight Control of a Tailless Fighter Aircraft, AIAA-99-4042
[12] Ilan Kroo, Aerodynamic Concepts for Future Aircraft, AIAA 99-3524
[13] Bogdan Popescu, Solutions for Improved Swept Wing Aircraft Designs, AIAA-99-1441
[14] Neal J. Pfeiffer, the Use of CFD in the Design Process for Configuration Drag, AIAA 2000-0380
[15] Y. Makino and T. lwamiya, Numerical Simulation and Aerodynamic Design of an SST Configuration with Nacelles, AIAA 2000-0126
[16] 方宝瑞，飞机气动布局设计，航空工业出版社，1997
[17] 王和平，现代飞机总体设计，西北工业大学
[18] 顾诵芬，飞机总体设计，北京航空航天大学出版社，2001．9
[19] 严恒元等，飞行器气动特性分析与工程计算，西北工业大学出版社，1990．6
[20] 朱自强等，应用计算流体力学，北京航空航天大学出版社，2001．1
[21] 陈再新等，空气动力学，航空工业出版社，1993
[22] 张彬乾，B．Laschka，前掠翼气动特性研究，西北工业大学学报，1989年7月
[23] 张彬乾，B．Laschka，前掠翼根部流动分离的控制，航空学报，1992年5月
[24] 张彬乾，鸭翼位置对前翼气动特性的影响，空气动力学学报，1990年8月
[25] 倪亚琴，先进战斗机的气动布局革新研究简析，空气动力学学报，1998年，第16卷
[26] 吕凤翥，C++语言程序设计，电子工业出版社，2002．2
[27] 莫蓉，周惠群，Unigraphics18版CAD应用基础，清华大学出版社，2002．1
[28] 范立钦，飞行动力学(飞机性能)，西北工业大学
[29] 胡兆丰，何植岱，高浩，飞行动力学，北京航空航天大学五系
[30] 衷红卫，有关前掠翼的一些气动特性，8410第三届气动布局会议文件，三院
三部，1992．5
[31]张立庄，王学俭，郭耀滨，张滨江，前掠翼低速空气动力学研究，中国航空科技文献，航空工业部
[32]叶炜梁，肖人熙，郭小良，前掠翼气动布局及低速纵向实验分析，科技报告，南京航空学院
[33]柳长安，非结构网格生成及二维非定常流场及悬挂物投放数值模拟，西北工业大学硕士论文
[34]刘谋佶，吕志咏等，边条翼与旋涡分离流，北京航空学院出版社1988．5
[35]前掠翼布局的低速试验研究报告，航空工业部六二七研究所
[36]前掠翼根部流动的改善报告，航空工业部六二七研究所
[37]郑遂，无尾战斗机气动布局初探，首届青年气动工作者学术报告会论文集，1997．11
[38]陈正举，浅析俄罗斯战斗机CY-37“金雕”前掠翼三翼面气动布局的先进性，沈阳航空工业学院学报，1999年6月，第16卷第2期
[39]章仲安，王略，带边条后掠翼融合体隐身布局的应用研究，气动实验与测量控制，1995年6月，第9卷，第2期
[40]曹名，陈国钧，通用航空飞机的三翼面布局研究，南京航空航天大学学报，1994年2月，第26卷，第1期
[41]宋文骢，谢品，郑遂，李玉璞，一种小展弦比高升力飞机的气动布局研究，中国工程科学，2001年8月，第3卷，第8期
[42]‘×××无人机总体设计技术研究’气动布局任务书，西北工业大学无人机所
[2] D.I.A. Poll and Cheng-Hao Qiu, Some effects of sweep direction and strakes for wings with sharp leading edges, The Aeronautical Journal, Volume 88 Number 878, October 1984.
[3] Zhang B Q, Yang Y N, An Investigation about Vertex Interference of the Canard Configuration at High Incidence. In: Proceedings of China-Japan Joint Symposium on Aerodynamics and Aircraft Design, Nanjing China, 1990, China Aviation Industry Press, 1990
[4] Mark A. Postdam, Blended Wing Body Analysis and Design, AIAA-97-2317
[5] Daniel G. Murri, Luat T. Nguyen, and Sue B. Grafton, Wind-Tunnel Free-Flight Investigation of a Model of a Forward-Swept-Wing Fighter Configuration, NASA Technical Paper 2230, 1984
[6] Takeshi OHNUKI and Nobuhiko KAMIYA, Transonic Investigations on High Aspect Ratio Forward- and Aft-Swept Wings, ICAS-88-2.2.1
[7] Spacht G, Bethpage, X-29:Managing an Integrated Advanced Technology Design, AIAA-86-2630
[8] D. Strohmever, W. Heinze, C. sterheld, L. Fornasier, Three Surface Aircraft - A Concept for Future Transport Aircraft, AIAA-00-0566
[9] J. H. McMasters, R. M. Cummings, Airplane Design - Past, Present and Future [Invited Paper], AIAA 2001-0535
[10] Barbara Pralio, Germana Vinelli, Giorgio Guglieri, Fulvia Quagliotti, Politecnico di Torino, Preliminary Design of a UAV Configuration, AIAA-2001-2422
[11] Rowena L. Eberhardi, David G. Ward, Indirect Adaptive Flight Control of a Tailless Fighter Aircraft, AIAA-99-4042
[12] Ilan Kroo, Aerodynamic Concepts for Future Aircraft, AIAA 99-3524
[13] Bogdan Popescu, Solutions for Improved Swept Wing Aircraft Designs, AIAA-99-1441
[14] Neal J. Pfeiffer, the Use of CFD in the Design Process for Configuration Drag, AIAA 2000-0380
[15] Y. Makino and T. lwamiya, Numerical Simulation and Aerodynamic Design of an SST Configuration with Nacelles, AIAA 2000-0126
[16] 方宝瑞，飞机气动布局设计，航空工业出版社，1997
[17] 王和平，现代飞机总体设计，西北工业大学
[18] 顾诵芬，飞机总体设计，北京航空航天大学出版社，2001．9
[19] 严恒元等，飞行器气动特性分析与工程计算，西北工业大学出版社，1990．6
[20] 朱自强等，应用计算流体力学，北京航空航天大学出版社，2001．1
[21] 陈再新等，空气动力学，航空工业出版社，1993
[22] 张彬乾，B．Laschka，前掠翼气动特性研究，西北工业大学学报，1989年7月
[23] 张彬乾，B．Laschka，前掠翼根部流动分离的控制，航空学报，1992年5月
[24] 张彬乾，鸭翼位置对前翼气动特性的影响，空气动力学学报，1990年8月
[25] 倪亚琴，先进战斗机的气动布局革新研究简析，空气动力学学报，1998年，第16卷
[26] 吕凤翥，C++语言程序设计，电子工业出版社，2002．2
[27] 莫蓉，周惠群，Unigraphics18版CAD应用基础，清华大学出版社，2002．1
[28] 范立钦，飞行动力学(飞机性能)，西北工业大学
[29] 胡兆丰，何植岱，高浩，飞行动力学，北京航空航天大学五系
[30] 衷红卫，有关前掠翼的一些气动特性，8410第三届气动布局会议文件，三院
三部，1992．5
[31]张立庄，王学俭，郭耀滨，张滨江，前掠翼低速空气动力学研究，中国航空科技文献，航空工业部
[32]叶炜梁，肖人熙，郭小良，前掠翼气动布局及低速纵向实验分析，科技报告，南京航空学院
[33]柳长安，非结构网格生成及二维非定常流场及悬挂物投放数值模拟，西北工业大学硕士论文
[34]刘谋佶，吕志咏等，边条翼与旋涡分离流，北京航空学院出版社1988．5
[35]前掠翼布局的低速试验研究报告，航空工业部六二七研究所
[36]前掠翼根部流动的改善报告，航空工业部六二七研究所
[37]郑遂，无尾战斗机气动布局初探，首届青年气动工作者学术报告会论文集，1997．11
[38]陈正举，浅析俄罗斯战斗机CY-37“金雕”前掠翼三翼面气动布局的先进性，沈阳航空工业学院学报，1999年6月，第16卷第2期
[39]章仲安，王略，带边条后掠翼融合体隐身布局的应用研究，气动实验与测量控制，1995年6月，第9卷，第2期
[40]曹名，陈国钧，通用航空飞机的三翼面布局研究，南京航空航天大学学报，1994年2月，第26卷，第1期
[41]宋文骢，谢品，郑遂，李玉璞，一种小展弦比高升力飞机的气动布局研究，中国工程科学，2001年8月，第3卷，第8期
[42]‘×××无人机总体设计技术研究’气动布局任务书，西北工业大学无人机所