一种翼身融合飞行器的失速特性研究

doi:10.7527/S1000-6893.2019.23176

流体力学与飞行力学

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一种翼身融合飞行器的失速特性研究

付军泉¹, 史志伟¹, 周梦贝¹, 吴大卫², 潘立军²

1. 南京航空航天大学航空学院, 南京 210016;
2. 中国商用飞机有限责任公司上海飞机设计研究院, 上海 201210

收稿日期:2019-05-22 修回日期:2019-07-03 出版日期:2020-01-15 发布日期:2019-09-09
通讯作者: 史志伟 E-mail:szwam@nuaa.edu.cn
基金资助:
江苏省研究生科研与实践创新计划项目（KYCX18_0250）；江苏高校优势学科建设工程资助项目

Stall characteristics research of blended-wing-body aircraft

FU Junquan¹, SHI Zhiwei¹, ZHOU Mengbei¹, WU Dawei², PAN Lijun²

1. College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;
2. Shanghai Aircraft Design and Research Institute, COMAC, Shanghai 201210, China

Received:2019-05-22 Revised:2019-07-03 Online:2020-01-15 Published:2019-09-09
Supported by:
Postgraduate Research &Practice Innovation Program of Jiangsu Province (KYCX18_0250); A Project Funded by the Priority Academic Program Development of Jiangsu Higher Education Institutions

摘要/Abstract

摘要： 翼身融合（BWB）布局飞行器作为下一代商用飞机的主要构型之一，越来越受到重视。对于翼身融合飞行器的研究主要针对其巡航状态的特性，而对其失速特性的研究较少。对一种翼身融合客机构型进行风洞试验研究，采用测力试验方法对其无增升装置的构型，以及具有翼梢小翼、前缘缝翼和机身上部双吊舱的组合部件构型下的纵向特性进行研究，特别是对其失速特性的分析，并通过二维粒子图像测试技术以及油流试验对其失速过程的流动机理进行研究。结果表明，无增升装置的基本构型下，翼身融合飞行器可以保持低速飞行，而各组合构型都具有提高最大升力系数的作用。对失速过程的分析表明，随着迎角的增大，飞机表面流场分离区域从翼梢开始逐渐向翼根以及机身发展，当外翼段完全处于分离区域时，飞机并不会马上失速，因为中心体同样具有提供升力的作用，且中心体的流动分离较外翼的流动分离更晚，所以当外翼在失速迎角出现升力损失时可以通过中心体的升力进行补偿，维持其低速飞行状态，真正的失速发生在中心体出现流动分离之后。

关键词: 翼身融合, 风洞试验, 失速特性, 流场分析, 测力分析

Abstract: As one of the main configurations of the next generation's commercial aircraft, Blended-Wing-Body (BWB) configuration aircraft has attracted more and more attention. While the research of BWB aircraft is mainly focused on the characteristics of its cruise phase, few have studied the stall characteristics. In this paper, the BWB is studied by wind tunnel test. The configuration of the non-lift device and the longitudinal characteristics of the composite components with winglet, leading edge slat, and double nacelles are studied by the force measurement method, especially the stall characteristics. The flow mechanism of the stall process is studied by the two-dimensional image testing technology. The results show that the BWB aircraft can maintain low-speed flight in the basic configuration without lift-up device, and the combination configuration has the effect of increasing lift coefficient. And with the increase of the angle of attack, the separation region gradually develops from the wing tip to the wing root and the fuselage. When the outer wing is completely in the separation region, the aircraft will not stall immediately. Because the centrosome also provides lift, and the flow separation of the centrosome is later than the outer wing. Therefore, when the outer wing causes lift loss at stall angle of attack, the lift of the centrosome can be compensated to maintain its low-speed flight phase. The real stall occurs after the flow separation of the centrosome.

Key words: blended-wing-body, wind tunnel test, stall characteristics, flow field analysis, force measurement analysis

中图分类号:

V211.3

付军泉, 史志伟, 周梦贝, 吴大卫, 潘立军. 一种翼身融合飞行器的失速特性研究[J]. 航空学报, 2020, 41(1): 123176-123176.

FU Junquan, SHI Zhiwei, ZHOU Mengbei, WU Dawei, PAN Lijun. Stall characteristics research of blended-wing-body aircraft[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2020, 41(1): 123176-123176.

参考文献 26

[1]	DEREK N J, DAVID G. Westland fixed wing aircraft 1915-1953[M]. Gloucestershire:Fonthill Media, 2018:50-70.
[2]	LIEBECK R H. Design of the blended wing body subsonic transport[J]. Journal of Aircraft, 2004, 41(1):10-25.
[3]	JORRIT V D, ROELOF V. Conceptual design and analysis of blended-wing-body aircraft[J]. Journal of Aerospace Engineering, 2014, 228(13):2452-2474.
[4]	ORDOUKHANIAN E, MADNI A M. Blended wing body architecting and design:Current status and future prospects[J]. Procedia Computer Science, 2014, 28:619-625.
[5]	朱自强,王晓璐,吴宗成,等. 民机的一种新型布局形式——翼身融合体飞机[J]. 航空学报, 2008, 29(1):49-59. ZHU Z Q,WANG X L,WU Z C,et al. A new type of transport-Blended wing body aircraft[J]. Acta Aeronautica et Astronautica Sinica, 2008, 29(1):49-59(in Chinese).
[6]	ROMAN D. Aerodynamic design challenges of the blended-wing-body subsonic transport[C]//Applied Aerodynamics Conference, 2000.
[7]	QIN N, VAVALLE A, MOIGNE A L, et al. Aerodynamic considerations of blended wing body aircraft[J]. Progress in Aerospace Sciences, 2004, 40(6):321-343.
[8]	蒋瑾, 钟伯文, 符松. 翼身融合布局飞机总体参数对气动性能的影响[J]. 航空学报, 2016, 37(1):278-289. JIANG J, ZHONG B W, FU S. Influence of overall configuration parameters on aerodynamic characteristics of a blended-wing-body aircraft[J]. Acta Aeronautica et Astronautica Sinica, 2016, 37(1):278-289(in Chinese).
[9]	PAULUS D, SALMON T, MOHR B. Configuration selection for a 450-passenger ultraefficient 2020 aircraft[C]//4th European Conference for Aerospace Sciences, 2011.
[10]	LI P F, ZHANG B Q, CHEN Y C, et al. Aerodynamic design methodology for blended wing body transport[J]. Chinese Journal of Aeronautics, 2012, 25(4):508-516.
[11]	LYU Z, MARTINS J R R A. Aerodynamic design optimization studies of a blended-wing-body aircraft[J]. Journal of Aircraft, 2014, 51(5):1604-1617.
[12]	GEOFFREY L, GRAHAM C. A design analysis of vertical stabilisers for blended wing body aircraft[J]. Aerospace Science and Technology, 2017, 64:237-252.
[13]	MUKHOPADHYAY V. Analysis, design and optimization of non-cylindrical fuselage for blended-wing-body (BWB) vehicle:AIAA-2002-5664[R]. Reston, VA:AIAA, 2002.
[14]	PAULUS D, WIRTH C, HORNUNG M. Blended wing body aircraft - recommendations from high lift and control surface design and optimization[C]//31st AIAA Applied Aerodynamics Conference. Reston, VA:AIAA, 2013.
[15]	RISCH T, COSENTINO G, REGAN C, et al. X-48B flight test progress overview[C]//AIAA Aerospace Sciences Meeting Including the New Horizons Forum & Aerospace Exposition. Reston, VA:AIAA, 2009.
[16]	CARTER M, VICROY D, PATEL D. Blended-wing-body transonic aerodynamics:Summary of ground tests and sample results (invited)[C]//47th AIAA Aerospace Sciences Meeting including the New Horizons Forum & Aerospace Exposition. Reston, VA:AIAA, 2009.
[17]	OLIVERIO E. Preliminary investigation on stall characteristics of a regional BWB for low speed approach[C]//35th AIAA Applied Aerodynamic Conference. Reston, VA:AIAA, 2017.
[18]	ROCKWELL D. Three-dimensional flow structure on delta wings at high angle-of-attack:Experimental concepts and issues[C]//31st AIAA Aerospace Sciences Meeting & Exhibit. Reston, VA:AIAA, 1993.
[19]	GURSUL I. Recent developments in delta wing aerodynamics[J]. The Aeronautical Journal, 2004, 108(1087):437-52.
[20]	OL M V, GHARIB M. Leading-edge vortex structure of nonslender delta wings at low Reynolds number[J]. AIAA Journal, 2003, 41(1):16-26.
[21]	BREITSAMTER C. Unsteady flow phenomena associated with leading-edge vortices[J]. Progress in Aerospace Sciences, 2008, 44(1):48-65.
[22]	KAPAROS P. Experimental investigation of DBD plasma actuators on a BWB aerial vehicle model[C]//2018 Flow Control Conference, 2018.
[23]	王铁城. 空气动力学实验技术[M]. 修订版. 北京:航空工业出版社,1995:174-188. WANG T C. Aerodynamic experimental techniques[M]. Revised edition. Beijing:Aviation Industry Press, 1995:174-188(in Chinese).
[24]	VISSER K D, NELSON R C. Measurement of circulation an vorticity in the leading-edge vortex of a delta wing[J]. AIAA Journal, 1993, 31(1):104-111.
[25]	VISSER K D, FERRERO M, NELSON R C. Physical consideration of leading-edge flows[C]//22nd Applied Aerodynamics Conference and Exhibit. Reston, VA:AIAA, 2004.
[26]	恽起麟. 对风洞试验数据精准度的要求[J]. 气动实验与测量控制,1994(1):66-72. YUN Q L. Requirement of accuracy for wind tunnel testing data[J]. Aerodynamic Experiment and Measurement & Control, 1994(1):66-72(in Chinese).

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主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

一种翼身融合飞行器的失速特性研究

Stall characteristics research of blended-wing-body aircraft

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