AERODYNAMIC CHARACTERISTICS OF NACA 0015 AIRFOIL HAVING DIFFERENT ASPECT RATIO WITH END PLATES

Seyhan M., Sarıoğlu M.

17th international conference of young scientists on energy and natural sciences issues , Kaunas, Litvanya, 24 - 28 Mayıs 2021, ss.1-7

  • Yayın Türü: Bildiri / Tam Metin Bildiri
  • Basıldığı Şehir: Kaunas
  • Basıldığı Ülke: Litvanya
  • Sayfa Sayıları: ss.1-7
  • Karadeniz Teknik Üniversitesi Adresli: Evet

Özet

An experimental study is carried out to investigate aerodynamic characteristics of NACA 0015 airfoil having different aspect ratio with the endplates. The aspect ratio (AR) is varied between 1 and 4 with an increment of 1. AR of the airfoil is the ratio of spanwise length to mean chord. Lift and drag forces are measured with the help of a six-axis load cell on the flow around NACA 0015 airfoil at Re= 7x104 and 1.1x105. This airfoil has a chord of 115 mm and a spanwise of 115 mm, 230 mm, 345 mm, and 460 mm. Force measurement results reveal that lift curves are significantly varied with increasing aspect ratio. Optimum L/D, indicating the aerodynamic performance of the airfoil, is obtained with aspect ratio of 4 at Re= 7x104 and 1.1x105. Stall angles for AR4, AR3, AR2, and AR1 are α = 10°, 11°, 12°, and 26°, repectively. Results indicates that the lift coeffecient performance enhances with increasing aspect ratios from 1 to 4 and stall angle significantly postpone with decreasing aspect ratios from 4 to 1.