翼身融合民机扰流板增升技术

doi:10.7527/S1000-6893.2019.23045

Abstract

Abstract: To meet the design requirements for the high-lift device of Blended-Wing-Body (BWB) civil aircraft with simplicity and high efficiency, the BWB high-lift configuration with three-element high-lift device is numerically simulated to study the mechanism of lift-enhancement and design principles of the drooped spoiler technology. The research results show that the reasonable design of the drooped spoiler can increase the design point lift coefficient of the BWB high-lift configuration by almost 20%. The lift-enhancement mechanism of the drooped spoiler is mainly concentrated on the control of the slot-jet, the energy distribution of the flow field, the circulation, and its distribution. The design principles of the drooped spoiler for BWB civil aircraft are as follows:the deflection of the drooped spoiler should be tangent to the upper surface of the flap; the gap width should be narrowed to enhance the circulation and move it forward; and the deflection of the internal spoiler should be limited to avoid premature separation. The study also shows that, with the influence of the three-dimensional effect of the high-lift device, the stronger the up-washing effect of spoiler deflected airfoils, the greater the lift loss of the three-dimensional high-lift device, showing an almost linear pattern of variation. Since it is simple to reconstruct and helps to simplify the flap operating mechanism, the drooped spoiler is a potential high-lift improvement technology, demonstrating in-depth research values and good application prospects.

Key words: blended-wing-body, civil aircraft, high-lift device, drooped spoiler, CFD

CLC Number:

V211.4

WANG Gang, ZHANG Minghui, MAO Jun, SANG Weimin, CHEN Zhenli, WANG Long, ZHANG Binqian. High-lift technology for spoiler on blended-wing-body civil aircraft[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2019, 40(9): 623045-623045.

References 25

[1]	LIN J C, MELTON L P, VIKEN S A, et al. High lift common research model for wind tunnel testing:An active flow control perspective:AIAA-2017-0319[R]. Reston, VA:AIAA, 2017.
[2]	GARNER P, MEREDITH P, STONER R. Areas for future CFD development as illustrated by transport aircraft applications:AIAA-1991-1527[R]. Reston, VA:AIAA, 1991.
[3]	陈迎春, 张美红, 张淼, 等. 大型客机气动设计综述[J]. 航空学报, 2019, 40(1):522759. CHEN Y C, ZHANG M H, ZHANG M, et al. Review of large civil aircraft aerodynamic design[J]. Acta Aeronautica et Astronautica Sinica, 2019, 40(1):522759(in Chinese).
[4]	CHU H B, ZHANG B Q, CHEN Y C, et al. Investigation of micro vortex generators on controlling flow separation over SCCH high-lift configuration[J]. Science China:Technological Sciences, 2012, 55(7):1943-1953.
[5]	NICKOL C, MCCULLERS L. Hybrid wing body configuration system studies:AIAA-2009-0931[R]. Reston, VA:AIAA, 2009.
[6]	OKONKWO P, SMITH H. Review of evolving trends in blended wing body aircraft design[J]. Progress in Aerospace Sciences, 2016, 82(3):1-23.
[7]	LEBOFSKY S, TING E, NGUYEN N T, et al. Aeroelastic modeling and drag optimization of flexible wing aircraft with variable camber continuous trailing edge flap:AIAA-2014-2443[R]. Reston, VA:AIAA, 2014.
[8]	褚胡冰, 张彬乾, 陈迎春, 等. 微型后缘装置增升效率及几何参数影响研究[J]. 航空学报, 2012, 33(3):381-389. CHU H B, ZHANG B Q, CHEN Y C, et al. Investigation on Mini-TED efficiency and impact of its geometrical parameters[J]. Acta Aeronautica et Astronautica Sinica, 2012, 33(3):381-389(in Chinese).
[9]	褚胡冰, 陈迎春, 张彬乾, 等. 增升装置微型涡流发生器数值模拟方法研究[J]. 航空学报, 2012, 33(1):11-21. CHU H B, CHEN Y C, ZHANG B Q, et al. Investigation of numerical simulation technique for micro vortex generators applied to high lift system[J]. Acta Aeronautica et Astronautica Sinica, 2012, 33(1):11-21(in Chinese).
[10]	陈迎春, 张攀峰, 王晋军. 扰流片分离流动特性的数值研究[J]. 北京航空航天大学学报, 2004, 30(12):1221-1224. CHEN Y C, ZHANG P F, WANG J J. Numerical simulation of separation flow around flaps with varied gap size[J]. Journal of Beijing University of Aeronautics and Astronautics, 2004, 30(12):1221-1224(in Chinese).
[11]	孙静, 杨广珺, 张彬乾. 带扰流板翼型的流场数值模拟[J]. 航空计算技术, 2006, 36(6):62-65. SUN J, YANG G J, ZHANG B Q. Numerical simulation of the flowfield of an airfoil with spoiler[J]. Aeronautical Computing Technique, 2006, 36(6):62-65(in Chinese).
[12]	KANJERE K, ZHANG X, HU Z, et al. Aeroacoustic investigation of deployed spoiler during steep approach landing:AIAA-2010-3992[R]. Reston, VA:AIAA, 2010.
[13]	JUNG U, BRIETSAMTER C. Aerodynamic wake investigations of high-lift transport aircraft with deployed spoilers[C]//27th International Congress of the Aeronautical Sciences (ICAS), 2010:19-24.
[14]	BREITSAMTER C. Wake vortex characteristics of transport aircraft[J]. Progress in Aerospace Sciences, 2011, 47(2):89-134.
[15]	ELSAYED O A, OMAR A A, ASRAR W, et al. Effect of differential spoiler settings (DSS) on the wake vortices of a wing at high-lift-configuration (HLC)[J]. Aerospace Science and Technology, 2011, 15(7):555-566.
[16]	SCHOLZ P, MAHMOOD S, CASPER M, et al. Design of active flow control at a drooped spoiler configuration:AIAA-2013-2518[R]. Reston, VA:AIAA, 2013.
[17]	徐琳, 田云, 刘沛清, 等. 大型飞机后缘铰链襟翼与扰流板下偏联合主动控制的二维绕流数值研究[J]. 民用飞机设计与研究, 2014, 4(1):52-57. XU L, TIAN Y, LIU P Q, et al. 2D numerical study based on active control of trailing edge high lift devices with downward deflection of spoiler for large aircraft[J]. Civil Aircraft Design & Research, 2014, 4(1):52-57(in Chinese).
[18]	WANG X L, WANG F X, LI Y L. Aerodynamic characteristics of high-lift devices with downward deflection of spoiler[J]. Journal of Aircraft, 2011, 48(2):730-735.
[19]	刘江, 郑隆乾, 白俊强, 等. 扰流板下偏对增升装置气动性能的影响及流动机理研究[J]. 西北工业大学学报, 2017, 35(5):813-820. LIU J, ZHENG L Q, BAI J Q, et al. Study on flow mechanism and aerodynamic characteristic of high-lift devices with drooped spoiler[J]. Journal of Northwestern Polytechnical University, 2017, 35(5):813-820(in Chinese).
[20]	WANG W, LIU P, TIAN Y, et al. Numerical study of the aerodynamic characteristics of high-lift droop nose with the deflection of fowler flap and spoiler[J]. Aerospace Science and Technology, 2016, 48(1):75-85.
[21]	CASPER M, SCHOLZ P. Active flow control on a two element high-lift airfoil with drooped spoiler:AIAA-2014-2147[R]. Reston, VA:AIAA, 2014.
[22]	SMITH A M O. High-lift aerodynamics[J]. Journal of Aircraft, 1975, 12(6):501-530.
[23]	褚胡冰, 张彬乾, 陈迎春, 等. 微型涡流发生器控制SCCH增升构型流动分离研究[J]. 中国科学:技术科学, 2012, 42(8):945-956. CHU H B, ZHANG B Q, CHEN Y C, et al. Investigation of micro vortex generators on controlling flow separation over SCCH high-lift configuration[J]. Science China:Technological Sciences, 2012, 42(8):945-956(in Chinese).
[24]	方宝瑞. 飞机气动布局设计[M]. 北京:航空工业出版社, 1997:518. FANG B R. Aircraft aerodynamic layout design[M]. Beijing:Aviation Industry Press, 1997:518(in Chinese).
[25]	飞机设计手册总编委会.飞机设计手册(第6册):气动设计[M]. 北京:航空工业出版社, 2002:65-66, 69, 71-72. Aircraft Design Manual General Editorial Board. Aircraft design manual 6:Aerodynamic design[M]. Beijing:Aviation Industry Press, 2002:65-66, 69, 71-72(in Chinese).

High-lift technology for spoiler on blended-wing-body civil aircraft

PDF (PC)

Knowledge

Abstract

Cite this article

share this article

References 25

Related Articles 15

Recommended Articles

Metrics

Comments

[1]	Di WANG, Yan LENG, Long YANG, Zhonghua HAN, Zhansen QIAN. Atmospheric turbulence effects on sonic boom propagation based on augmented Burgers equation [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(2): 626318-626318.
[2]	Xiong HUANG, Shiru QU, Heng ZHANG, Xiantiao CHEN. Stall performance of high-lift configuration of large civil aircraft with slat de-icing [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(1): 627077-627077.
[3]	XIAHOU Tangfan, CHEN Jiangtao, SHAO Zhidong, WU Xiaojun, LIU Yu. Model validation metrics for CFD numerical simulation under aleatory and epistemic uncertainty [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(8): 25716-025716.
[4]	LUO Jiajie, SONG Wenbin. Nested collaborative optimization of laminar wing and its high-lift devices [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(8): 125377-125377.
[5]	CEN Fei, LIU Zhitao, JIANG Yong, GUO Tianhao, ZHANG Lei, KONG Yinan. Unsteady aerodynamics modeling of civil transport configuration under extreme flight conditions [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(8): 125582-125582.
[6]	ZHANG Xinyue, XI Xulong, LIU Xiaochuan, BAI Chunyu. Experimental study on crash characteristics of typical metal civil aircraft fuselage structure [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(6): 526234-526234.
[7]	WANG Yupeng, TIAN Wenpeng, SONG Pengfei, XIA Feng, FENG Jianmin. Research and verification of comprehensive acceleration technology for civil aircraft full-scale fatigue test [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(5): 224919-224919.
[8]	ZHANG Liwen, SONG Wenping, HAN Zhonghua, QIAN Zhansen, SONG Bifeng. Recent progress of sonic boom generation, propagation, and mitigation mechanism [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(12): 25649-025649.
[9]	WANG Haifeng, DENG Feng, LIU Xueqiang, QIN Ning. Gust load alleviation control based on jets for natural laminar airfoil [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(11): 526767-526767.
[10]	YUAN Jisen, SUN Jue, LI Lingyu, YU Shenghao, NIE Han, GAO Liangjie, HAN Zhonghua, QIAN Zhansen. Progress of supersonic aircraft laminar flow layout design and evaluation technologies [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(11): 526316-526316.
[11]	YAN Chao. Achievements and predicaments of CFD in aeronautics in past forty years [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(10): 526490-526490.
[12]	WANG Di, QIAN Zhansen, LENG Yan. High-order scheme discretization of sonic boom propagation model based on augmented Burgers equation [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(1): 124916-124916.
[13]	FU Junquan, SHI Zhiwei, GENG Xi, ZHU Jiachen, WANG Lishuang, WU Dawei, PAN Lijun. Longitudinal stability of blended-wing-body aircraft based on experimental bifurcation analysis [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(1): 124931-124931.
[14]	WANG Zihang, LYU Hongqiang. Research on lightning electromagnetic field based on CFD high-precision algorithm [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2021, 42(S1): 726366-726366.
[15]	LI Peng, CHEN Jianqiang, DING Mingsong, HE Xianyao, ZHAO Zhong, DONG Weizhong. Framework design of NNW-HyFLOW hypersonic flow simulation software [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2021, 42(9): 625718-625718.