为满足现代大型飞机增升装置简洁高效的设计需求,以典型三段翼型为对象,采用数值模拟研究在后缘襟翼上增加微型后缘装置(mini-TED)以提高增升装置效率的可行性;给出了微型后缘装置的作用原理,获得了微型后缘装置位置、长度、偏度等几何参数对增升和升阻性能的影响规律。研究结果表明:微型后缘装置明显改变了襟翼后缘弯度,对襟翼流动产生有利诱导作用,拓展加长了增升装置的有效"气动弦长",是一种附加气动襟翼。其几何参数设计原则是:以长度l≤1.5%c(c为干净翼型弦长)、位于95%襟翼弦向位置前较为合适;偏度则可根据起降等飞行状态进行选择。与四段及其以上增升装置相比,微型后缘装置具有增升效果显著、结构简单、附加重量小和易于工程实现等优点,是一种极具潜力的新型增升技术,具有深入的研究价值和良好的应用前景。
In order to meet the design requirements of high lift system with high efficiency and simple structure for modern large aircraft, this paper selects a typical three element airfoil, and, based on numerical simulation, studies the feasibility of mini-trailing edge device (mini-TED) to improve the aerodynamic performance of the lift system and analyzes its physical mechanism and the impact of its geometrical parameters, including the mini-TED fixing position, length and deflection angle. The study shows that the mini-TED changes the curvature of the trailing edge and increases the effective aerodynamic chord length for a high lift system, acting like an additional aerodynamic flap. Mini-TED with geometrical parameters of length l≤1.5%c (c is the chord length) and fixing position before 95% length of the flap is suitable, and its deflection angle can be adjusted based on different flying states. Compared with the four or more element high lift system, mini-TED features remarkable lift enhancement effect, simple structure, light additional height, and easy application in engineering. It possesses attractive potential as a new lift enhancement technique.
[1] Gamer P L, Meredith P T, Stoner R C. Areas for future CFD development as illustrated by transport aircraft applications. AIAA-1991-1527, 1991.
[2] Henne P A, Gregg Ⅲ R D. New airfoil design concept. AIAA-1991-46028, 1991.
[3] Thompson B E, Lotz R D. Divergent trailing edge airfoil flow. AIAA-1996-47040, 1996.
[4] Li G. Introduction of mini-TED for civil aircraft. International Aviation, 2006(10): 62-63. (in Chinese) 李果. 商用飞机机翼后缘设计新思路. 国际航空, 2006(10): 62-63.
[5] Singh M K, Dhanalakshmi K, Chakrabartty S K. Navier-Stokes analysis of airfoils with Gurney flap. AIAA-2007-27285, 2007.
[6] Myose R, Heron I, Papadakis M. Effect of Gurney flaps on a NACA0011 airfoil. AIAA-1996-0059, 1996.
[7] Zhou H. Numerical analysis of effect of mini-TED on aerodynamic characteristics of airfoils in transonic flow. Acta Aeronautica et Astronautica Sinica, 2009, 30(8): 1367-1373. (in Chinese) 周华. Mini-TED改变翼型跨声速性能的数值分析.航空学报, 2009,30(8): 1367-1373.
[8] Ouyang Y F, Pen X Z, Qiu C R. Study on the apply of cruise flap. 6th Straits Seminar of Aeronautics and Astronautics. Xi'an: Northwestern Polytechnical University, 2008: 142-145. (in Chinese) 欧阳一方, 彭小忠, 邱传仁. 巡航襟翼技术的应用研究. 第六届海峡两岸航空航天学术研讨会论文集. 西安: 西北工业大学, 2008: 142-145.
[9] Li Y C, Wang J J, Hua J. Experimental investigations on the effects of divergent trailing edge and Gurney flaps on a supercritical airfoil. Aerospace Science and Technology, 2007, 11 (2/3): 91-99.
[10] Papadakis M, Myose R Y.Experimental investigation of Gurney flaps on a two element general aviation airfoil. AIAA-1997-728, 1997.
[11] Gardner A D, Nitzsche J, Neumann J, et al. Adaptive load redistribution using mini-TEDs.25th International Congress of the Aeronautical Sciences. 2006.
[12] Richter K, Rosemann H. Numerical investigation on the aerodynamic effect of mini-TEDs on the AWIATOR aircraft at cruise conditions. 25th International Congress of the Aeronautical Sciences.2006.
[13] Hansen H. Application of mini trailing edge devices in the AWIATOR project. 5th ONERA-DLR Aerospace Symposium.2003.
[14] Balaji R, Bramkamp F, Hesse M, et al. Effect of flap and slat riggings on 2-d high-lift aerodynamics. AIAA-2006-19391, 2006.
[15] Zhou R X, Gao Y W, Quan C X, et al. The analyses of aerodynamic characters of multi-elenment airfoil with Gurney flap. Acta Aerodynamica Sinica, 2002, 20(6): 174-178. (in Chinese) 周瑞兴, 高永卫, 全承信, 等. 具有Gurney襟翼的多段翼型空气动力特性分析. 空气动力学学报, 2002, 20(6): 174-178.
CJA