叶片表面粗糙条件下钝尾缘翼型优化设计

摘要/Abstract

摘要： 利用粒子群算法结合XFOIL软件，进行了钝尾缘翼型型线优化设计。平移优化后，在翼型吸力面距前缘0.1c(c为弦长)处添加一高0.015c、宽0.04c的凸台，得到表面粗糙钝尾缘改型，并数值研究其升阻力系数、升阻比、压力系数和流场特性。结果表明：粗糙S812翼型钝尾缘优化后，尾缘厚度为0.039 8c，尾缘厚度在上下翼面的分配比为1∶13.16；升力系数在计算攻角范围内显著增大，升阻比在17.2°攻角之前显著增大，最大升阻比增大明显；钝尾缘处的漩涡对吸力面的气流造成下洗作用。

关键词: 粗糙, 翼型, 钝尾缘改型, 优化设计

Abstract: Optimization design of blunt trailing-edge airfoil profiles was carried out by using particle swarm optimization algorithm coupling with the software XFOIL. A lug boss with the height of 0.015c (c is chord) and the width of 0.04c was added on the optimized airfoils through translating the suction surface coordinates on the position of 0.1c away from the leading-edge, and the blunt trailing-edge modification of rough airfoils was obtained. Lift and drag coefficients, lift-drag ratios, pressure coefficients, and flow characteristics before and after blunt trailing-edge optimization were investigated numerically. The results indicate that after blunt trailing-edge optimization of rough S812 airfoil, the trailing-edge thickness is as 0.039 8c, and the thickness distribution ratio is as 1∶13.16. The lift coefficient within calculating angle and lift-drag ratio before the attack angle of 17.2° increase remarkably, and the maximum lift-drag ratio is significantly increased. The vertex at airfoil’s blunt trailing-edge causes the downwash effects on the airflow of suction surfaces.

Key words: rough, airfoil, blunt trailing-edge modification, optimization design

中图分类号:

TK83

张旭1,2;张孟洁1;王格格1;李伟2,3;阮江涛1. 叶片表面粗糙条件下钝尾缘翼型优化设计[J]. 中国机械工程.

ZHANG Xu1,2;ZHANG Mengjie1;WANG Gege1;LI Wei2,3;RUAN Jiangtao1. Optimization Design of Blunt Trailing-edge Airfoil under Conditions of Rough Blades[J]. China Mechanical Engineering.

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