低雷诺数下柔性翼型气动性能分析
发布时间：2018-10-24 19:22
【摘要】：基于流固耦合方法对吸力面5%至95%弦长处为三段柔性结构的NACA0012翼型绕流进行了数值模拟,研究了不同弹性模量下柔性翼型的气动性能和结构响应.结果表明:在大攻角下,翼面变形影响着翼型表面的非定常流场,起到延缓失速和提高升力的作用;失速后柔性翼的升力系数下降得较为缓慢,且柔性越大,升力系数下降得越平缓;适当减小弹性模量能够提高翼型的气动性能,然而弹性模量过小反而不利于翼型气动性能的提升,并且翼面会产生大幅度的振动.
[Abstract]:Based on the fluid-solid coupling method, the aerodynamic performance and structural response of a NACA0012 airfoil with 5% to 95% chord strength over a three-segment flexible structure are studied. The aerodynamic performance and structural response of the flexible airfoil with different elastic modulus are studied. The results show that the wing surface deformation affects the unsteady flow field of the airfoil surface at the large angle of attack, delays the stall and increases the lift force, and the lift coefficient of the flexible wing decreases slowly after the stall, and the greater the flexibility is, The lower the lift coefficient is, the more the aerodynamic performance of the airfoil can be improved by decreasing the elastic modulus. However, the lower the elastic modulus is, the less the aerodynamic performance of the airfoil is, and the larger vibration will occur on the wing surface.
【作者单位】： 北京航空航天大学能源与动力工程学院 航空发动机气动热力国家级重点实验室;先进航空发动机协同创新中心;
【基金】：国家自然科学基金资助项目(51106003)
【分类号】：V211.3
[Abstract]:Based on the fluid-solid coupling method, the aerodynamic performance and structural response of a NACA0012 airfoil with 5% to 95% chord strength over a three-segment flexible structure are studied. The aerodynamic performance and structural response of the flexible airfoil with different elastic modulus are studied. The results show that the wing surface deformation affects the unsteady flow field of the airfoil surface at the large angle of attack, delays the stall and increases the lift force, and the lift coefficient of the flexible wing decreases slowly after the stall, and the greater the flexibility is, The lower the lift coefficient is, the more the aerodynamic performance of the airfoil can be improved by decreasing the elastic modulus. However, the lower the elastic modulus is, the less the aerodynamic performance of the airfoil is, and the larger vibration will occur on the wing surface.
【作者单位】： 北京航空航天大学能源与动力工程学院 航空发动机气动热力国家级重点实验室;先进航空发动机协同创新中心;
【基金】：国家自然科学基金资助项目(51106003)
【分类号】：V211.3
【相似文献】
相关期刊论文 前10条
1 孙可明,梁冰,朱月明;考虑解吸扩散过程的煤层气流固耦合渗流研究[J];辽宁工程技术大学学报(自然科学版);2001年04期
2 王建军,李其汉,朱梓根,陆明万,张雄;自由液面大晃动的流固耦合数值分析方法研究进展[J];力学季刊;2001年04期
3 郭术义,陈举华;流固耦合应用研究进展[J];济南大学学报(自然科学版);2004年02期
4 王建;金志浩;;输流管道流固耦合非线性动力学分析[J];沈阳化工学院学报;2007年04期
5 王征;吴虎;贾海军;;流固耦合力学的数值研究方法的发展及软件应用概述[J];机床与液压;2008年04期
6 李艳华;柳贡民;马俊;;考虑流固耦合的典型管段结构振动特性分析[J];振动与冲击;2010年06期
7 郝婷s，
本文编号：2292319
本文链接：https://www.wllwen.com/kejilunwen/lxlw/2292319.html
