Enhancement of airfoil performance by rotating cylinder | ||
| Al-Qadisiyah Journal for Engineering Sciences | ||
| Volume 14, Issue 2, June 2021, Pages 89-94 PDF (772.65 K) | ||
| Document Type: Research Paper | ||
| DOI: 10.30772/qjes.v14i2.748 | ||
| Authors | ||
| Mohammed Sadeq Kadhim* ; Dhafer A. Hamza | ||
| Department of Mechanical Engineering, Collage of Engineering, University of Al-Qadisiyah, Ad-Diwaniyah, Iraq. | ||
| Abstract | ||
| This study used a NACA 6409 smooth wing section. Its performance is compared to an enhanced design incorporating a revolving cylinder on the upper airfoil surface. The boundary conditions for the present work were Reynolds (105), and the attack angles were (0,2,4,6,8,10,12,14,16). A turbulence model was developed (SST K-), one of the aerodynamics models. This model is well-suited for sensing flow near a wall. The cylinder was evaluated at three positions (25,50,75) percent of the chord's length. The results indicated that position (25 percent C) was optimal, as it resulted in a 24.45 percent increase in lift coefficient at the angle of attack (12). And when the results were compared to those of other studies, they revealed a significant agreement. | ||
| Keywords | ||
| Airfoil; Enhancement; Rotating Cylinder; Performance; NACA6409 | ||
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