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针对格尼襟翼低头力矩较大的问题,提出了后缘弧形襟翼概念作为格尼襟翼的改进构型,该构型通过襟翼背风面形成的局部高压区域来提供附加抬头力矩。基于CFD数值计算模型分析了弧形襟翼的气动力特性和襟翼附近的流场特征。计算结果表明:弧形襟翼的低头力矩明显低于相同高度的格尼襟翼;相比格尼襟翼,升力系数和阻力系数虽略有减小,但升阻比增大;尖部向流场中延伸能够进一步降低襟翼的低头力矩。相比格尼襟翼,弧形襟翼更有利于在飞行器设计中实际应用。
Abstract：Since the pitch moment of airfoils was increased significantly by Gurney flap,a type of cambered flaps which were equipped at the trailing edge of airfoils was proposed as a modified configuration of Gurney flap. The cambered flap could provide additional negative pitch moment by local relative higher pressure region behind it. The aerodynamics characteristics of cambered flap as well as flowfield near the flap were analyzed based on CFD method. The result indicated lower pitch moment of cambered flap over Gurney flap. In comparison with Gurney flap,although the lift and drag coefficient of the cambered flap were slightly decreased,the lift-drag-ratio was increased. The pitch moment was decreased further as the tip of flap extended into flowfield backward. So the cambered flap seems more beneficial to the practical application for aircraft design than Gurney flap.
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基本信息:
DOI：10.13645/j.cnki.f.d.20170822.003
中图分类号:V211.41
引用信息:
[1]崔钊,张毅,张宏林等.后缘弧形襟翼的气动特性研究[J].飞行力学,2018,36(01):7-11.DOI:10.13645/j.cnki.f.d.20170822.003.
基金信息: