翼型气动性能数值分析  

Numerical analysis of the aerodynamic performance of airfoils

作　　者：李国勤 孙丹 艾延廷[1,2] 周海仑 王志[1,2] 

机构地区：[1]沈阳航空航天大学航空航天工程学部(院),沈阳110136 [2]沈阳航空航天大学辽宁省航空推进系统先进测试技术重点实验室,沈阳110136

出　　处：《沈阳航空航天大学学报》2017年第6期27-32,39,共7页Journal of Shenyang Aerospace University

基　　金：国家自然科学基金(项目编号:51675351)

摘　　要：利用Spalart-Allmaras湍流模型对NACA0006翼型和NACA6412两种翼型进行了气动性能数值研究,比较分析了两种翼型在不同攻角和不同马赫数下的气动性能,研究了攻角和马赫数对两种翼型升力系数、阻力系数以及升阻比的影响。研究结果表明,在所研究攻角范围内,当马赫数为0.8时,NACA0006和NACA6412两翼型的最佳攻角分别为2°和4°,NACA0006翼型的升阻比随攻角的变化更加明显;在所研究马赫数范围内,当攻角为4°时,当马赫数分别为0.6和0.5时,NACA0006和NACA6412两翼型升阻比最大,NACA6412翼型的升阻比随马赫数的变化更加明显。In this paper,aerodynamic performance of the NACA0006 airfoil and NACA6412 airfoil w as analyzed by the Spalart-Allmaras turbulence model. The aerodynamic performance of the tw o airfoils under different attack angles and different M ach numbers w ere compared and analyzed. The effects of the angles and M ach numbers on the lift coefficient,drag coefficient and lift-drag ratio w ere further investigated. The results show that the best angles of the NACA0006 airfoil and the NACA6412 airfoil are 2° and 4° respectively w hen M ach number is 0. 8. The life-drag ratio of the NACA0006 airfoil changes obviously w ith the increase of attack angle. The NACA0006 airfoil and the NACA6412 airfoil have the biggest life-drag ratio corresponding to 0. 6 and 0. 5 respectively w hen α is 4°. The life-drag ratio of NACA6412 airfoil is more obvious than that of NACA0006 airfoil w ith the increase of M ach number.

关 键 词：翼型 气动性能 马赫数 升阻比 数值分析 

分 类 号：V224[航空宇航科学与技术—飞行器设计]