后缘连续变弯度对跨声速翼型气动特性的影响

doi:10.7527/S1000-6893.2015.0161

流体力学与飞行力学

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后缘连续变弯度对跨声速翼型气动特性的影响

郭同彪, 白俊强, 杨体浩

西北工业大学航空学院, 西安 710072

收稿日期:2015-03-09 修回日期:2015-05-23 出版日期:2016-02-15 发布日期:2015-06-24
通讯作者: 白俊强,男,博士,教授,博士生导师。主要研究方向:飞行器总体气动布局设计、部件气动力设计、多学科优化设计、计算流体力学理论和应用。Tel:029-88492174,E-mail:junqiang@nwpu.edu.cn E-mail:junqiang@nwpu.edu.cn
作者简介:郭同彪,男,硕士研究生。主要研究方向:飞行器气动优化设计。Tel:15809270907,E-mail:812558997@qq.com
基金资助:
国家"973"计划(2014CB744800)

Influence of continuous trailing-edge variable camber on aerodynamic characteristics of transonic airfoils

GUO Tongbiao, BAI Junqiang, YANG Tihao

School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China

Received:2015-03-09 Revised:2015-05-23 Online:2016-02-15 Published:2015-06-24
Supported by:
National Basic Research Program of China(2014CB744800)

摘要/Abstract

摘要：

针对后缘连续变弯度对跨声速翼型气动特性的影响进行了研究。首先不考虑翼型后缘连续变弯度,基于搭建的优化设计系统对跨声速翼型进行气动减阻优化设计,通过添加不同的约束优化得到两种跨声速翼型:无激波翼型和超临界翼型。然后在这两种翼型的基础上,以后缘偏转角度为设计变量、以阻力系数最小为目标,针对不同的升力系数分别进行优化设计,并根据优化结果深入分析后缘连续变弯度对这两种翼型极曲线特性的影响机理。优化结果表明:无激波翼型与超临界翼型相比,其设计点处的气动特性较好,但鲁棒性较差;升力系数小于设计升力系数时,应用后缘连续变弯度后,无激波翼型的极曲线特性明显提高,减阻最高达到3.9%,而超临界翼型的极曲线特性提高不明显;升力系数大于设计升力系数时,应用后缘连续变弯度后,无激波翼型和超临界翼型的极曲线特性都明显提高,减阻分别达到2.4%~18.1%和1.7%~13.2%。

关键词: 后缘连续变弯度, 无激波翼型, 超临界翼型, 优化设计, 鲁棒性, 极曲线

Abstract:

The influence of continuous trailing-edge variable camber on the aerodynamic characteristics of transonic airfoils is investigated. Before the continuous trailing-edge variable camber is considered, the aerodynamic drag reduction optimization design of the transonic airfoil is carried out based on the optimization design system constructed in this paper. With different constraints added, two kinds of transonic airfoils are obtained, namely the shock-free airfoil and the supercritical airfoil. Then the optimization design is conducted based on the two airfoils at different lift coefficients, by taking the deflection angle of the trailing-edge as the design variable and the minimum drag coefficient as the objective. And the effect of the continuous trailing-edge variable camber on the drag polar of these two kinds of transonic airfoils is investigated and analyzed according to the optimization results. The results of the optimization design show that the aerodynamic characteristics of the shock-free airfoil are better than those of the supercritical airfoil at the design point, but the robustness is worse. Besides, when the lift coefficient is lower than the design lift coefficient, the drag polar characteristic of the shock-free airfoil can be improved greatly with the continuous trailing-edge variable camber applied, thus the drag coefficient is reduced by up to 3.9%. However, the situation of supercritical airfoil is different. The results also demonstrate that when the lift coefficient exceeds the design lift coefficient, the continuous trailing-edge variable camber method can significantly improve the drag polar performance of both airfoils with the drag coefficients of them being reduced by 2.4%-18.1% and 1.7%-13.2% respectively.

Key words: continuous trailing-edge variable camber, shock-free airfoil, supercritical airfoil, optimization design, robustness, polar

中图分类号:

V211.41⁺2

郭同彪, 白俊强, 杨体浩. 后缘连续变弯度对跨声速翼型气动特性的影响[J]. 航空学报, 2016, 37(2): 513-521.

GUO Tongbiao, BAI Junqiang, YANG Tihao. Influence of continuous trailing-edge variable camber on aerodynamic characteristics of transonic airfoils[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2016, 37(2): 513-521.

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后缘连续变弯度对跨声速翼型气动特性的影响

Influence of continuous trailing-edge variable camber on aerodynamic characteristics of transonic airfoils

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