内吹式襟翼控制机理和失速特性

张刘; 姜裕标; 何萌; 陈洪; 高立华

doi:10.7638/kqdlxxb-2021.0008

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内吹式襟翼控制机理和失速特性

研究论文 | 更新时间：2026-05-28

- 内吹式襟翼控制机理和失速特性
- Stall characteristics and circulation control of internally blown flap
- 空气动力学学报 2021年39卷第5期页码：53-62
- 作者机构：
  
  1. 中国空气动力研究与发展中心空气动力学国家重点实验室,绵阳,621000
  2. 中国空气动力研究与发展中心低速空气动力研究所,绵阳,621000
- 作者简介：
  
  张刘*（1986-），男，安徽阜阳人，助理研究员，研究方向：飞行器流动控制方向. E-mail：lzh2607@126.com
- 基金信息：
  
  中国空气动力研究与发展中心基础和前沿技术研究基金资助项目（FFTRF20171001）
- DOI：10.7638/kqdlxxb-2021.0008
  中图分类号： V211.41
- 纸质出版：2021
- 稿件说明：
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张刘, 姜裕标, 何萌, 等. 内吹式襟翼控制机理和失速特性[J]. 空气动力学学报, 2021, 39(5): 53−62.

ZHANG Liu, JIANG Yubiao, HE Meng, et al. Stall characteristics and circulation control of internally blown flap[J]. 2021, 39(5): 53-62.
张刘, 姜裕标, 何萌, 等. 内吹式襟翼控制机理和失速特性[J]. 空气动力学学报, 2021, 39(5): 53−62. DOI： 10.7638/kqdlxxb-2021.0008

ZHANG Liu, JIANG Yubiao, HE Meng, et al. Stall characteristics and circulation control of internally blown flap[J]. 2021, 39(5): 53-62. DOI： 10.7638/kqdlxxb-2021.0008.

摘要

短距起降运输机对增升装置提出了更高要求，常规机械式增升装置已无法满足，内吹式襟翼系统是当今固定翼飞机最有效的动力增升形式。为推动该技术的工程应用，基于雷诺平均N-S方程，对某加装60°偏角无缝襟翼的亚声速翼型在环量控制作用下的流场进行数值模拟，研究了其在不同吹气动量系数下的气动特性及流动形态，分析了不同环量控制阶段增升机理、失速特性和吹气动量系数对失速特性影响规律。结果表明：内吹式襟翼增升控制效率（升力系数增量与吹气动量系数的比值）较高，在临界吹气动量系数下可达70，此时相较于无吹气状态，升力增加约125%；主翼上由于环量增加产生的升力增量是翼型升力增量的主要来源，约占总升力增量的78%；吹气动量系数增加可造成翼型气动中心后移；附面层分离控制区主要通过消除襟翼上的流动分离增加升力，超环量控制区升力的增加是由于尾缘下游的射流效应使流线进一步偏转而实现的；随吹气动量增加，附面层分离控制区的失速迎角提前，超环量控制区失速迎角略微推迟。

Abstract

With the special demand of STOL performance for transport plane

the regularly mechanical devices for lift enhancement could no longer satisfy the requirement of maximum available lift coefficient. The internally blown flap system is the most efficient way of powered lift-enhancement for fixed-wing aircraft. In order to promote the engineering application of this technology

the aerodynamic characteristics and flow structure of a 2D subsonic 60° seamless flap with varying moment coefficient are obtained based on RANS equations. The mechanism of circulation control and stall in different regime have been analysed. It reveals that

the lift-enhancement efficiency (the ratio between the gain in lift yielded by the active system and the required blowing momentum) of this system is high

which reaches the highest value of 70 at the critical momentum

and the lift coefficient increase by 125% compared to that of without blowing. With blowing

the lift coefficient increases due to the circulation increases on the main wing surface

the increment is about 78% of the total lift coefficient increment. The location of aerodynamic center of the airfoil moves backward with the increase of blowing flux. Further

blowing delays flow separation at the boundary-layer control regime

resulting in a significant lift coefficient improvement. The increment of lift coefficient is achieved by a further defection of the streamlines due to the jet effect downstream of the trailing edge at the super-circulation regime. With the blowing flux increase

the stall angle decrease in the boundary layer regime and increase at the super-circulation regime.

关键词

Keywords

references

BALL T, TURNER S, MARSHALL D D. Short takeoff performance using circulation control[C ] //46 th AIAA Aerospace Sciences Meeting and Exhibit, Reno, Nevada: 2008.

GRIFFIN H A, GONZALEZ L F, SRINIVAS K. Computational fluid dynamics analysis of externally blown flap configuration for transport aircraft[J]. Journal of Aircraft, 2008, 45(1): 172-184.DOI: 10.2514/1.30842.

SUSSMAN M, REED J, OKEEFE J, et al. USB environment assessment based on YC-14 flight test measurements[C ] //Proc of the V/STOL C onference, Palo Alto, CA, USA. Reston, Virigina: AIAA, 1977. doi: 10.2514/6.1977-593

HENRI C. Device for deflecting a stream of elastic fluid projected into an elastic fluid: US, US2052869 A[P]. 1936.

ENGLAR R J, HUSON G G. Development of advanced circulation control wing high-lift airfoils[J]. Journal of Aircraft, 1984, 21(7): 476-483.DOI: 10.2514/3.44996.

ENGLAR R J. Low-speed aerodynamic characteristics of a small, fixed-trailing-edge circulation control wing configuration fitted to a supercritical airfoil. Biochemistry[R]. DTNSRDC Rept. ASED-81/08, March 1981.

Englar R J. Development of an advanced no-moving parts high-lift airfoil[C]//ICAS/AIAA Aircraft Systems and Technology Conference, ICAS-82-6.5. 4, 1982: 951-959.

ENGLAR R J, SMITH M J, KELLEY S M, et al. Application of circulation control to advanced subsonic transport aircraft, part I - airfoil development[J]. Journal of Aircraft, 1994, 31(5): 1160-1168.DOI: 10.2514/3.56907.

ENGLAR R J, SMITH M J, KELLEY S M, et al. Application of circulation control to advanced subsonic transport aircraft. Part II - Transport application[J]. Journal of Aircraft, 1994, 31(5): 1169-1177.DOI: 10.2514/3.46627.

ENGLAR R J, APPLEGATE C A. Circulation control—A bibliography of DTNSRDC research and selected outside references (Jan. 1969 to Dec. 1983): AD-A146 966[R]. David Taylor Naval Ship RD Center Rept. (DTNSRDC) 84/052, Bethesda, MD, 1984.

BURNAZZI M, RADESPIEL R. Design and analysis of a droop nose for coanda flap applications[J]. Journal of Aircraft, 2014, 51(5): 1567-1579.DOI: 10.2514/1.C032434.

POTT-POLLENSKE M, ALVAREZ-GONZALES J, DOBRZYNSKI W. Effect of slat gap on farfield radiated noise and correlation with local flow characteristics[C]//9th AIAA/CEAS Aeroacoustics Conference, Hilton Head (USA): 2003.

LEE-RAUSCH E, VATSA V, RUMSEY C. Computational analysis of dual radius circulation control airfoils[C ] //3rd AIAA Flow Control Conference, San Francisco, California. Reston, Virigina: AIAA, 2006. doi: 10.2514/6.2006-3012

JONES G, YAO C S, ALLAN B. Experimental investigation of a 2D supercritical circulation-control airfoil using particle image velocimetry[C ] //3rd AIAA Flow Control Conference, San Francisco, California . Reston, Virginia: AIAA, 2006. doi: 10.2514/6.2006-3009

JENSCH C, PFINGSTEN K C, RADESPIEL R, et al. Design aspects of a gapless high-lift system with active blowing[C]//Deutscher Luft- und Raumfahrtkongress 2009. DGLR, Bonn, Germany: 2009.

JENSCH C, PFINGSTEN K C, RADESPIEL R. Numerical investigation of leading edge blowing and optimization of the slot geometry for a circulation control airfoil[C ] //New Results in Numerical and Experimental Fluid Mechanics VII, 2010. doi: 10.1007/978-3-642-14243-7_23

LIU Y, SANKAR L, ENGLAR R, et al. Computational evaluation of the steady and pulsed jet effects on the performance of a circulation control wing section[C ] //42nd AIAA Aerospace Sciences Meeting and Exhibit, Reno, Nevada. Reston, Virigina: AIAA, 2004. doi: 10.2514/6.2004-56

LIU Y, SANKAR L, ENGLAR R, et al. Numerical simulations of the steady and unsteady aerodynamic characteristics of a circulation control wing airfoil[C ] //39th Aerospace Sciences Meeting and Exhibit, Reno, NV. Reston, Virginia: AIAA, 2001. doi: 10.2514/6.2001-704

ZHU Z Q, WU Z C. Study of the circulation control technology[J]. Acta Aeronautica et Astronautica Sinica, 2016, 37(2): 411-428. (in Chinese).

KONG B, WANG F X, ZHOU T. The aerodynamic design of seamlessly camber-variable airfoil based on circulation control[J]. Acta Aerodynamica Sinica, 2013, 31(5): 583-586. (in Chinese).

WANG M X, SUN W P, QIN H J. Optimization design of an internal blown flap used in large amphibian[J]. Acta Aeronautica et Astronautica Sinica, 2016, 37(1): 300-309. (in Chinese).

CHEN G. Characteristics analysis and design optimization of blowing seamless flap[J]. Journal of Wuhan University of Technology (Transportation Science Engineering), 2016, 40(3): 418-422. (in Chinese).

LIU R, BAI J Q, QIU Y S, et al. Effects of geometrical parameters of internal blown flap and its optimal design[J]. Journal of Northwestern Polytechnical University, 2020, 38(1): 58-67. (in Chinese).

JIANG Y B, ZHANG L, HUANG Y, et al. Lift response characteristics of a circulation control airfoil with internally blown flap[J]. Acta Aeronautica et Astronautica Sinica, 2018, 39(7): 64-72. (in Chinese).

JIANG Y B, WANG W B, ZHAO G Y, et al. Experimental investigation on blowing control airfoil influenced by ground effect. ACTA Aerodynamica Sinica, 2020, 38(05): 887-895. (in Chinese)DOI: 10.7638/kqdlxxb-2020.0101.

ENGLAR R J, WILLIAMS R M. Test techniques for high-lift two-dimensional airfoils with boundary and circulation control for application to rotary wing aircraft[J]. Canadian Aeronautics and Space Journal. 1975, 10(3): 93-108.

CHIN V, PETERS D, SPAID F, et al. Flowfield measurements about a multi-element airfoil at high Reynolds numbers [C ] //AIAA 24th Fluid Dynamics Conference. Washington D C: AIAA, 1993. doi: 10.2514/6.1993-3137

JONES G, ENGLAR R. Advances in pneumatic controlled high lift systems through pulsed blowing[C]//21st AIAA Applied Aerodynamics Conference, Orlando, Florida. Reston, Virigina: AIAA, 2003. doi:10.2514/6.2003-3411

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