基于前缘缝翼微型后缘装置的多段翼型被动流动控制

doi:10.7527/S1000-6893.2017.120650

流体力学与飞行力学

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基于前缘缝翼微型后缘装置的多段翼型被动流动控制

张振辉, 李栋, 杨茵

西北工业大学翼型叶栅空气动力学国家重点实验室, 西安 710072

收稿日期:2016-07-27 修回日期:2017-01-19 出版日期:2017-05-15 发布日期:2017-02-13
通讯作者: 李栋 E-mail:ldgh@nwpu.edu.cn
基金资助:
国家自然科学基金（11072200）；中欧国际合作项目MARS

Passive flow control of multi-element airfoils using slat mini-trailing edge device

ZHANG Zhenhui, LI Dong, YANG Yin

National Key Laboratory of Science and Technology on Aerodynamic Design and Research, Northwestern Polytechnical University, Xi'an 710072, China

Received:2016-07-27 Revised:2017-01-19 Online:2017-05-15 Published:2017-02-13
Supported by:
National Natural Science Foundation of China (11072200);MARS Project Co-Funded by European Union and Chinese MIIT

摘要/Abstract

摘要：

以麦道航空公司的三段增升构型为研究模型，采用剪切应力输运（SST）k-ω湍流模型在C-H型多块结构网格上求解二维非定常雷诺平均Navier-Stokes方程，研究了前缘缝翼微型后缘装置（MTED）在多段翼型被动流动控制中的应用。由于MTED改变了实际的缝翼缝道参数，因此首先研究了作为主要改变量的缝道宽度对该三段翼型气动性能的影响，当缝道宽度从参考构型的2.95%c增加至3.98%c时，最大总升力系数约减小4.61%。当在不同缝道宽度基本构型上增加相同MTED时，计算结果表明它对各个翼段的影响定性一致，即前缘缝翼升力增加、主翼升力减小以及后缘襟翼升力基本不变化。这些升力变化的综合作用是：MTED构型线性段总升力系数的变化不大，失速段的变化取决于缝道宽度，当缝道宽度为3.98%c时，高度为0.50%c的MTED构型的最大总升力系数约增加6.98%。

关键词: 多段翼型, 被动流动控制, 前缘缝翼, 微型后缘装置(MTED), 缝道宽度

Abstract:

Based on the McDonnell Douglas Aerospace three-element high lift configuration, two-dimensional unsteady Reynolds averaged Navier-Stokes equations together with shear stress transport (SST) k-ω turbulence model are employed on the multi-block structured grid of C-H type to investigate application of slat mini-trailing edge device (MTED) to passive flow control of multi-element airfoils. Considering that the actual slat slot parameters would be changed due to addition of slat MTED, effects of the slat gap, as the primary parametric variation, on the aerodynamic characteristics of the studied three-element airfoil are investigated. The results show that the maximum total lift coefficient is reduced by about 4.61% when the slat gap increases from 2.95%c to 3.98%c. The same slat MTED presents qualitatively consistent impacts on individual elements of these basic configurations with different slat gaps, namely increasing slat lift, decreasing main-element lift and almost negligible effects on flap lift. The combination of these lift changes leads to very slight change in the linear region of the total lift coefficient, but more significant variation depending on the slat gap in the stall region. When the slat gap is 3.98%c, the maximum total lift coefficient increases by about 6.98% for the configuration with the slat MTED height being 0.50%c.

Key words: multi-element airfoil, passive flow control, slat, mini-trailing edge device (MTED), slat gap

中图分类号:

V211.3

张振辉, 李栋, 杨茵. 基于前缘缝翼微型后缘装置的多段翼型被动流动控制[J]. 航空学报, 2017, 38(5): 120650-120650.

ZHANG Zhenhui, LI Dong, YANG Yin. Passive flow control of multi-element airfoils using slat mini-trailing edge device[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2017, 38(5): 120650-120650.

参考文献

[1] 李丽雅. 大型飞机增升装置技术发展综述[J]. 航空科学与技术, 2015, 26(5):1-10. LI L Y. Review of high-lift device technology development on large aircrafts[J]. Aeronautical Science and Technology, 2015, 26(5):1-10 (in Chinese).
[2] VAN DAM C P. The aerodynamic design of multi-element high-lift systems for transport airplanes[J]. Progress in Aerospace Sciences, 2002, 38(2):101-144.
[3] 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.
[4] ROSS J C, STORMS B L, CARRANNANTO P G. Lift-enhancing tabs on multielement airfoils[J]. Journal of Aircraft, 1995, 32(3):649-655.
[5] 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).
[6] LIN J C, ROBINSON S K, MCGHEE R J, et al. Separation control on high Reynolds number multi-element airfoils[C]//10th Applied Aerodynamics Conference. Reston:AIAA, 1992.
[7] MELTON L P, YAO C S, SEIFERT A. Application of excitation from multiple locations on a simplified high-lift system[C]//2nd AIAA Flow Control Conference. Reston:AIAA, 2004.
[8] LITTLE J, NISHIHARA M, ADAMOVICH I, et al. Separation control from the flap of a high-lift airfoil using DBD plasma actuators[C]//4th Flow Control Conference. Reston:AIAA, 2008.
[9] HOLL T, ALEXANDER K, GIACOPINELLI P. Detached-eddy simulation of pulsed blowing actuation on the flap of a high-lift configuration[C]//29th AIAA Applied Aerodynamics Conference. Reston:AIAA, 2011.
[10] PAPADAKIS M, MYOSE R Y, MATALLANA S. Experimental investigation of Gurney flaps on a two-element general aviation, airfoil[C]//35th Aerospace Sciences Meeting & Exhibit. Reston:AIAA, 1997.
[11] CARRANNANTO P G, STORMS B L, ROSS J C, et al. Navier-Stokes analysis of lift-enhancing tabs on multi-element airfoils[J]. Aircraft Design, 1998, 1(3):145-158.
[12] 周瑞兴, 高永卫, 金承信, 等. 具有Gurney襟翼的多段翼型空气动力特性分析[J]. 空气动力学学报, 2002, 20(2):174-178. ZHOU R X, GAO Y W, JIN C X, et al. The analyses of aerodynamic characters of multi-element airfoil with Gurney flap[J]. Acta Aerodynamica Sinica, 2002, 20(2):174-178 (in Chinese).
[13] RUMSEY C L, YING S X. Prediction of high lift:Review of present CFD capability[J]. Progress in Aerospace Sciences, 2002, 38(2):145-180.
[14] KLAUSMEYER S M, LIN J C. Comparative results from a CFD challenge over a 2D three-element high-lift airfoil:NASA-TM-112858[R]. Washington, D.C.:NASA, 1997.
[15] CHIN V D, PETERS D W, SPAID F W, et al. Flowfield measurements about a multi-element airfoil at high Reynolds numbers:AIAA-1993-3137[R]. Reston:AIAA, 1993.
[16] VALAREZO W O, DOMINIK C J, MCGHEE R J, et al. High Reynolds number configuration development of a high-lift airfoil[R]. Paris:AGARD, 1992.
[17] PETROSINO F, MINGIONE G, CAROZZA A, et al. Ice accretion model on multi-element airfoil[J]. Journal of Aircraft, 2011, 48(6):1913-1920.
[18] TYAN M, PARK J, KIM S, et al. Subsonic airfoil and flap hybrid optimization using multi-fidelity aerodynamic analysis:AIAA-2012-5453[R]. Reston:AIAA, 2012.
[19] 王运涛, 孟德虹, 邓小刚. 多段翼型高精度数值模拟技术研究[J]. 空气动力学学报, 2013, 31(1):88-93. WANG Y T, MENG D H, DENG X G. High-order numerical study of complex flow over multi-element airfoil[J]. Acta Aerodynamica Sinica, 2013, 31(1):88-93 (in Chinese).
[20] RENUKUMAR B, BRAMKAMP F D, HESSE M, et al. Effect of flap and slat riggings on 2-D high-lift aerodynamics[J]. Journal of Aircraft, 2006, 43(5):1259-1271.

E-mail：hkxb@buaa.edu.cn

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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

基于前缘缝翼微型后缘装置的多段翼型被动流动控制

Passive flow control of multi-element airfoils using slat mini-trailing edge device

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