GAW-1翼型前后缘变弯度气动性能研究
收稿日期: 2015-03-17
修回日期: 2015-06-16
网络出版日期: 2015-06-29
Aerodynamic performance of GAW-1 airfoil leading-edge and trailing-edge variable camber
Received date: 2015-03-17
Revised date: 2015-06-16
Online published: 2015-06-29
传统增升装置主要用于提高飞机起降气动性能。利用计算流体力学(CFD)的方法,引入了通用飞机翼型的前后缘变弯装置的概念,数值模拟了GAW-1翼型在爬升状态时,前缘变弯装置、后缘襟翼/副翼偏转以及前后缘装置综合偏转对翼型气动特性的影响。研究表明,前缘变弯装置可以有效地改善翼型的失速特性,失速迎角提高了3°左右,最大升力系数提高了4.56%;同时提高升阻比50%~120%;但在设计升力系数下,升力系数和阻力系数都略微减小。另一方面,后缘变弯装置可以改变最大升阻比所对应的迎角,以及在小迎角时,提高升力系数6%左右。翼型综合偏转可以在小迎角时增加升力系数,在大迎角时增加升阻比。
陆维爽 , 田云 , 刘沛清 , 王涛 , 张良富 . GAW-1翼型前后缘变弯度气动性能研究[J]. 航空学报, 2016 , 37(2) : 437 -450 . DOI: 10.7527/S1000-6893.2015.0185
The traditional high-lift device is used to improve the taking-off and landing aerodynamic performance of aircraft. By using the method of computational fluid dynamics(CFD), an idea of leading-edge and trailing-edge variable camber devices based on general aviation airfoil is introduced. The influences of leading-edge variable camber device, trailing-edge flap/aileron, and both leading-edge and trailing-edge variable camber devices of GAW-1 airfoil in the climbing state on airfoil aerodynamic performances are studied respectively. Learning from the results, leading-edge variable camber device can effectively improve the airfoil stall characteristics, increasing the angle of stall by about 3°, and the maximum lift coefficient has been increased by 4.56%. At the same time, the lift-to-drag ratio has been increased by 50% to 120%. But with the design lift coefficient, both lift coefficient and drag coefficient have been decreased. On the other hand, the function of trailing-edge variable camber device is to reposition the maximum of lift-to-drag ratio and to increase the lift coefficient by about 6% at a small angle of attack. Composite deflection of airfoil can increase lift coefficient at small angle of attack and increase lift-to-drag ratio at large angle of attack.
[1] NGUYEN N, PRECUP N, URNES J, SR, et al. Experimental investigation of a flexible wing with a variable camber continuous trailing edge flap design[C]//32nd AIAA Applied Aerodynamics Conference. Reston:AIAA, 2014.
[2] LEBOFSKY S, TING E, NGUYEN N. Aeroelastic modeling and drag optimization of aircraft wing with variable camber continuous trailing edge flap[C]//32nd AIAA Applied Aerodynamics Conference. Reston:AIAA, 2014.
[3] URNES J, SR, MORRIS C, SHEAHAN J, et al. Control system design for a variable camber continuous trailing edge flap system on an elastic wing[C]//55th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Reston:AIAA, 2014.
[4] URNES J, SR, NGUYEN N, IPPOLITO C, et al. A mission-Adaptive variable camber flap control system to optimize high lift and cruise lift-to-drag ratios of future N+3 transport aircraft[C]//51st AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition. Reston:AIAA, 2013.
[5] SINAPIUS M, MONNER H P, KINTSCHER M, et al. DLR's morphing wing activities within the European network[J]. Procedia IUTAM, 2014, 10(1):416-426.
[6] AHMED S, GUO S. Optimal design and analysis of a wing with morphing high lift devices[C]//54th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Reston:AIAA, 2013.
[7] DI MATTEO N, GUO S, MORISHIMA R. Optimization of leading edge and flap with actuation system for a variable camber wing[C]//53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference. Reston:AIAA, 2012.
[8] DI MATTEO N, GUO S, LI D. Morphing trailing edge flap for high lift wing[C]//52nd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference. Reston:AIAA, 2011.
[9] DI MATTEO N, GUO S, AHMED S, et al. Design and analysis of a morphing flap structure for high lift wing[C]//51st AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Reston:AIAA, 2010.
[10] PERERA M, HE Y, GUO S. Structural and dynamic analysis of seamless aeroelastic wing[C]//51st AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Reston:AIAA, 2010.
[11] PERERA M, GUO S. Optimal design of a seamless aeroelastic wing structure[C]//50th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Reston:AIAA, 2009.
[12] MONNER H P, KINTSCHER M, LORKOWSKI T, et al. Design of a smart droop nose as leading edge high lift system for transportation aircrafts[C]//50th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Reston:AIAA, 2009.
[13] LI D C, GUO S J, HE Y Y, et al. Nonlinear aeroelastic analysis of morphing flap[J]. International Journal of Bifurcation and Chaos, 2012, 22(5):125009-125020.
[14] YOKOZEKI T, SUGIURA A. Development of variable camber morphing airfoil using corrugated structure[J]. Journal of Aircraft, 2014, 51(3):1023-1029.
[15] YOKOZEKI T, SUGIURA A. Development and wind tunnel test of variable camber morphing wing[C]//22nd AIAA/ASME/AHS Adaptive Structures Conference. Reston:AIAA, 2014.
[16] 陈钱, 白鹏, 尹维龙, 等. 可连续光滑偏转后缘的变弯度翼型气动特性分析[J]. 空气动力学学报, 2010, 28(1):46-53. CHEN Q, BAI P, YIN W L, et al. Analysis on the aerodynamic characteristics of variable camber airfoils with continuous smooth morphing trailing edge[J]. Acta Aerodynamics Sinica, 2010, 28(1):46-53(in Chinese).
[17] 尹维龙. 关节式准柔性后缘翼型的气动特性分析[J]. 哈尔滨工业大学学报, 2010, 42(11):1758-1761. YIN W L. Aerodynamic characteristics of multi-sectional variable trailing-edge airfoil[J]. Journal of Harbin Institute of Technology, 2010, 42(11):1758-1761(in Chinese).
[18] 韩占忠, 王敬, 兰小平. FLUENT流体工程仿真计算实例与应用[M]. 1版. 北京:北京理工大学出版社, 2004:21-22. HAN Z Z, WANG J, LAN X P. The case and application of FLUENT fluid engineering simulation[M]. 1st ed. Beijing:Beijing Institute of Technology Press, 2004:21-22(in Chinese).
[19] WENTZ W H, JR, SEETBARAM H C, FISCKO K A. Force and pressure tests of the GA(W)-1 airfoil with a 20% aileron and pressure tests with 30% Fowler flap:NASA CR-2833[R]. Washington, D.C.:NASA, 1977.
[20] WENTZ W H, JR, SEETBARAM H C, FISCKO K A. Pressure distribution for the GA(W)-2 airfoil with 20% aileron 25% slotted flap and 30% Fowler flap:NASA CR-2948[R]. Washington, D.C.:NASA, 1978.
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