应用协同射流控制的临近空间螺旋桨高增效方法

doi:10.7527/S1000-6893.2013.0492

流体力学与飞行力学

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应用协同射流控制的临近空间螺旋桨高增效方法

朱敏, 杨旭东, 宋超, 宋文萍

西北工业大学翼型叶栅空气动力学国防科技重点实验室, 陕西西安 710072

收稿日期:2013-09-12 修回日期:2013-12-16 出版日期:2014-06-25 发布日期:2014-01-17
通讯作者: 杨旭东，Tel.：029-88491419 E-mail：xdyang@nwpu.edu.cn E-mail:xdyang@nwpu.edu.cn
作者简介:朱敏男，博士研究生。主要研究方向：理论与计算流体力学。Tel：029-88491419 E-mail：zhumin01010305@163.com；杨旭东男，博士，副教授。主要研究方向：理论与计算流体力学、设计空气动力学。Tel：029-88491419 E-mail：xdyang@nwpu.edu.cn；宋文萍女，博士，教授，博士生导师。主要研究方向：理论与计算流体力学、设计空气动力学。Tel：029-88491144 E-mail：wpsong@nwpu.edu.cn
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

ZHU Min, YANG Xudong, SONG Chao, SONG Wenping

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

Received:2013-09-12 Revised:2013-12-16 Online:2014-06-25 Published:2014-01-17
Supported by:
National Natural Science Foundation of China (11272263, 11302177)

摘要/Abstract

摘要：

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。

关键词: 流动控制, Navier-Stokes方程, 螺旋桨, 协同射流, 喷口动量系数, 临近空间, 效能比

Abstract:

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.

Key words: flow control, Navier-Stokes equations, propeller, co-flow jet, jet momentum coefficient, near space, efficiency ratio

中图分类号:

V211.3

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.

ZHU Min, YANG Xudong, SONG Chao, SONG Wenping. High Synergy Method for Near Space Propeller Using Co-flow Jet Control[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2014, 35(6): 1549-1559.

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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

应用协同射流控制的临近空间螺旋桨高增效方法

High Synergy Method for Near Space Propeller Using Co-flow Jet Control

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