亚音速流动中球形和锥体凹陷和凸起对翼型性能的影响

IF 0.9 Q3 ENGINEERING, AEROSPACE Journal of Aerospace Technology and Management Pub Date : 2021-01-01 DOI:10.1590/JATM.V13.1219
Zahra Mehtar, Afaq Altaf
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引用次数: 1

摘要

在这项研究中,表面特征,如酒窝和颠簸被引入到一个NACA 0012翼型的表面,以研究其对边界层分离的影响,特别是在高攻角。设计了六种改进的翼型,具有球形和锥体形状的酒窝和凸起。利用Ansys Fluent软件对这些模型在亚音速下进行了计算流体动力学(CFD)分析。分析采用0 ~ 15°变迎角(AOA)下的剪切应力输运k - ω湍流模型。生成速度等高线和流线。并对升力系数、阻力系数和升阻比进行了计算和分析。结果表明,所有表面改性均导致流动分离和再循环延迟。所有表面改性也导致阻力在15°时减小。除锥形凸起外,所有设计都提高了15°时的升阻比(L/D)性能。结果表明,凹痕特征优于凸起特征,球形特征优于锥体特征。在
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Influence of Spherical and Pyramidical Dimples and Bumps on Airfoil Performance in Subsonic Flow
In this study, surface features such as dimples and bumps are introduced to the surface of a NACA 0012 airfoil to study their effect on boundary layer separation, particularly at high angles of attack. Six modified airfoils were designed with dimples and bumps of spherical and pyramidical shapes. A computational fluid dynamics (CFD) analysis was conducted on these models at subsonic flow using Ansys Fluent. The analysis used the Shear Stress Transport k – ω turbulence model at a varying angle of attack (AOA) from 0 to 15°. The velocity contours and streamlines were generated. Also, the lift coefficient, drag coefficient and the lift-to-drag performance ratio were computed and analyzed. The results showed that all surface modifications led to delayed flow separation and flow recirculation. All surface modification also resulted in a decrease in drag at 15°. All designs, except pyramidical protrusions, increased the lift-to-drag ratio (L/D) performance at 15°. It was found that dimples are better than bumps and spherical features are better than pyramidical ones. on
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CiteScore
2.00
自引率
0.00%
发文量
16
审稿时长
20 weeks
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