摘要
基于NREL S809翼型,研究尾翼摆角对于翼型气动性能的影响.通过对比升阻力系数的模拟值与实验值,排除了网格质量对翼型气动性能的影响,验证了利用S-A(Spalart-Allmaras)湍流模型对风力机翼型进行计算的有效性,确定了合理的模拟方案,分析了翼型的气动性能.在此基础上,将S809翼型进行了尾缘变形,生成S809上摆-5°、下摆5°、10°及15°这4种变形翼型.再利用CFD(computational fluid dynamics)软件对它们进行数值计算,分析了各个翼型升阻力系数及流场特性.研究表明,随着尾缘下摆角度的增加,变形翼型上下表面压差逐渐增大,下摆翼型在升阻力特性方面有较大改善.但随着翼型下摆角度的增大,翼型产生分离涡的攻角却随之减小,更易失速.而上摆翼型升阻力特性及失速特性均不如原始翼型.
NREL S809 airfoil was selected as an object to study the impact of trailing edge angle on its aerodynamic performances.The simulation results were compared with the experiment ones to rule out the grid quality effects on aerodynamic performance,the effectiveness of S-A （Spalart-Allmaras）turbulence model was verified and a reasonable simulation scheme was made sure to analyze the airfoil well and truly.On this basis,the S809 trailing edge swing angle was altered to generate S809 -5＆#176;,5＆#176;,10＆#176;,15＆#176;deformed airfoils.Then the CFD software was used to analyze numerically each airfoil’s aerodynamic characteristics.With the increase of trailing edge swing angle,the differential pressure on the upper and lower surfaces of the airfoil becomes bigger.So for the positive swing angle airfoils the lift and resistance characteristics are improved,however,when the airfoil swing angle is increased,the angle of attack becomes smaller and the separation vortex would appear.For negative swing angle airfoils,all of the lift,resistance and stalling characteristics are worse.
出处
《上海理工大学学报》
CAS
北大核心
2015年第4期332-338,共7页
Journal of University of Shanghai For Science and Technology
基金
国家自然科学基金资助项目(E51176129)
上海市教委科研创新(重点)资助项目(13ZZ120
13YZ066)
教育部高等学校博士学科点专项科研基金(博导类)资助项目(20123120110008)
关键词
翼型
尾缘
数值模拟
气动性能
airfoil
trailing edge
numerical simulation
aerodynamic performance
作者简介
第一作者：季康（1991-），男，硕十研究毕．研究方向：翼型气动数值模拟．E-mail：iikang2441@163．com
通信作者：李春（1963-），男，教授．研究方向：风力机设计优化及风能利用．E-mail：lichunusst@163．com
