应用协同射流控制的临近空间螺旋桨高增效方法
收稿日期: 2013-09-12
修回日期: 2013-12-16
网络出版日期: 2014-01-17
基金资助
国家自然科学基金（11272263，11302177）
High Synergy Method for Near Space Propeller Using Co-flow Jet Control
Received date: 2013-09-12
Revised date: 2013-12-16
Online published: 2014-01-17
Supported by
National Natural Science Foundation of China (11272263, 11302177)
基于雷诺平均Navier-Stokes方程与多块搭接网格技术，数值模拟了协同射流（CFJ）翼型及桨叶的黏性绕流，分析了CFJ技术的增升减阻效果及工作机理。研究了CFJ的功率及效能比的分析方法，量化分析了CFJ的能量利用率。开展了喷口大小、喷口动量系数等参数对CFJ翼型性能的影响规律研究，并在此基础上开展了应用CFJ的临近空间螺旋桨高增效方法研究。结果表明：数值模拟结果与实验值吻合良好，在不同状态下，CFJ控制技术均能显著改善翼型气动性能。其中，最大升力系数提高了60%~130%；阻力系数降低了100%~440%，部分小迎角工况甚至出现负阻力系数，升阻比显著提高；翼型失速特性明显改善，失速迎角提高了近10°；能量利用率高，效能比可达440%。最终，在最优参数条件设置下，采用基于CFJ控制技术的临近空间螺旋桨可提高效率5%以上。
朱敏 , 杨旭东 , 宋超 , 宋文萍 . 应用协同射流控制的临近空间螺旋桨高增效方法[J]. 航空学报, 2014 , 35(6) : 1549 -1559 . DOI: 10.7527/S1000-6893.2013.0492
Based on the Reynolds-averaged Navier-Stokes equations and multi-block grid technology, a numerical simulation is implemented of a high performance airfoil and near space propeller using the co-flow jet (CFJ) flow control method, based on which the mechanism and performance of CFJ technology are studied. In order to quantify the energy efficiency of the CFJ technology, analysis methods of power demand and energy efficiency are proposed. Based on the influence of different jet slot sizes, jet momentum coefficient and other parameters on the CFJ technology performance are investigated, the research of high synergy method for near space propeller by co-flow jet flow control are carried out. It is shown that the numerical simulation results agree well with the experimental data. In different states, CFJ technology can significantly improve the aerodynamic performance of the airfoil: the maximum lift coefficient may increase by 60%-130%, the drag coefficient may be reduced by 100%-440%, and even negative drag coefficient may appear at low angles of attack, so much so that the lift-drag ratio is significantly improved. Also, the airfoil stall characteristics are significantly improved with the stall angle of attack increasing by nearly 10°. Furthermore, the power demand is very low and the energy efficiency is enhanced up to 440%. Finally, due to these improvements, the efficiency of the near space propeller using CFJ technology is increased by more than 5% for the proposed optimal jet slot size and jet momentum coefficient.
[1] Liu B J, Yang X N, Shen X L, et al. Experimental investigation of separation flow control using vortex-generating devices[J]. Journal of Engineering Thermophysics, 1998, 19(4): 444-448. (in Chinese) 刘宝杰, 杨晓宁, 沈遐龄, 等. 几种前缘流动控制的实验研究[J]. 工程热物理学报, 1998, 19(4): 444-448.
[2] Gu Y S, Li B B, Cheng K M. On the jet vector deflection based on active flow control technique[J]. Journal of Experimental Mechanics, 2012, 27(1): 87-91. (in Chinese) 顾蕴松, 李斌斌, 程克明. 基于主动流动控制的射流矢量偏转技术[J]. 实验力学, 2012, 27(1): 87-91.
[3] Luo Z B, Xia Z X.Advances in synthetic jet technology and applications in flow control[J].Advances in Mechanics, 2005, 35(2): 220-234. (in Chinese) 罗振兵, 夏智勋. 合成射流技术及其在流动控制中应用的进展[J]. 力学进展, 2005, 35(2): 220-234.
[4] Gilarranz J L.Development of high-power, compact synthetic jet actuators for flow separation control dissertation.Texas: Dwight Look College of Engineering, Texas A＆M University, 2001.
[5] Zhang P F, Wang J J, Shi W Y, et al. Experimental study on the separation control by plasma actuator in subsonic flow[J]. Journal of Experiments in Fluid Mechanics, 2007, 21(6): 35-39. (in Chinese) 张攀峰, 王晋军, 施威毅, 等.等离子体激励低速分离流动控制实验研究[J].实验流体力学, 2007, 21(6): 35-39.
[6] Englar R J. Circulation control for high lift and drag generation on STOL aircraft[J]. Journal of Aircraft, 1975, 12(5): 457-463.
[7] Roth J R. Aerodynamic flow acceleration using paraelectrie and peristaltic electrohydrodynamic effects of a one atmosphere uniform glow discharge plasma[J]. Physics of Plasmas, 2003, 10(5): 2117-2126.
[8] Ports J, Moreau E, Touchard G.Asymmetric surface dielectric barrier discharge in air at atmospheric pressure: electrical properties and induced airflow characteristics[J]. Journal of Physics D: Applied Physics, 2005, 38(19): 3635-3642.
[9] Zha G C, Paxton C. A novel airfoil circulation augment flow control method using co-flow jet, AIAA-2004-2208. Reston: AIAA, 2004.
[10] Zha G C, Carroll B F, Paxton C, et al. High performance airfoil using co-flow jet flow control, AIAA-2005-1260. Reston: AIAA, 2005.
[11] Zha G C, Gao W. Analysis of jet effects on co-flow jet airfoil performance with integrated propulsion system, AIAA-2006-0102. Reston: AIAA, 2006.
[12] Dano B, Zha G C, Castillo M. Experimental study of co-flow jet airfoil performance enhancement using discrete jets, AIAA-2011-0941. Reston: AIAA, 2011.
[13] Zha G C, Gao W, Paxton C. Jet effects on co-flow jet airfoil performance[J]. AIAA Journal, 2007, 45(6): 1222-1231.
[14] Kirk D D, Zha G C. Experimental investigation of jet mixing mechanism of co-flow jet airfoil, AIAA-2010-4421. Reston: AIAA, 2010.
[15] Han Z H. Efficient method for simulation of viscous flows past helicopter rotors and active flow control. Xi'an: School of Aeronautics, Northwestern Polytechnical University, 2007. (in Chinese) 韩忠华. 旋翼绕流的高效数值计算方法及主动流动控制研究. 西安: 西北工业大学航空学院, 2007.
[16] Florian R. Improved two-equation k-ω turbulence model for aerodynamic flow, NASA TM103975. Washington, D.C.: NASA, 1992.
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