Clark-Y uçak kanadı profiline sahip girdap üreteçlerinin konik NACA 0020 kanat üzerindeki etkisi

Year 2024, , 776 - 784, 15.07.2024

Mehmet Seyhan , Aleyna Çolak , Mustafa Sarıoğlu

https://doi.org/10.28948/ngumuh.1437429

Abstract

Bu deneysel çalışmada Clark-Y uçak kanadı şekilli girdap üreteçleri ve üçgensel girdap üreteçlerinin (GÜ) konik geriye ok açılı kanat üzerindeki etkileri incelenmiştir. Bu çalışmanın amacı, GÜ'lerin yerleşimi ve tasarımının kanadın aerodinamik özelliklerini nasıl etkilediğini anlamaktır. Testler, ters dönen aero-şekilli girdap üreteçleri x/c = 0.1, 0.2, 0.3, 0.4 ve 0.5 konumlarında, geleneksel girdap üreteçleri x/c=0.1 konumunda kullanılarak Re = 6.0x104 Reynolds sayısında gerçekleştirilmiştir. 0° ila 30° arasında değişen hücum açılarındaki kuvvetleri ölçmek için bir yük hücresi kullanılmıştır. Clark-Y uçak kanadı şekilli GÜ’lerin konumu x/c=0.1'den 0.5'e değişmesiyle CLmax değerinin ve bu değerin elde edildiği hücum açılarının düştüğü görülmektedir. Çalışmadan elde edilen optimal sonuçlar, Clark-Y uçak kanadı şekilli GÜ’lerin x/c=0.1 konumunda, temel modele kıyasla CLmax değerinde %37.5 ve aerodinamik performansta yaklaşık %55 oranında önemli bir artış sağladığını göstermektedir. Düşük hücum açılarında Clark-Y uçak kanadı şekilli GÜ’ler daha iyi taşıma sağlarken, yüksek hücum açılarında üçgensel GÜ’ler daha iyi taşıma oluşturmuştur. Üçgensel GÜ’lerin sürükleme katsayısı düz modele ve uçak kanadı şekilli GÜ’lere göre daha yüksektir. Bu da uçak kanat şekilli GÜ’lerin aerodinamik performansının özellikle düşük açılarda daha yüksek olmasına neden olmaktadır. Bu durum Clark-Y kanat profiline sahip GÜ'lerin kanadın aerodinamik performansını artırmada etkili olduğunu göstermektedir.

Keywords

Clark-Y şekilli girdap üreteci, NACA 0020, Konik geriye ok açılı kanat, Akış kontrol

The effect of Clark-Y airfoil vortex generators on tapered NACA 0020 wing

Abstract

In the experimental study, the effects of vortex generators (VGs) having Clark-Y airfoil and triangular VGs were investigated. The aim was to understand how the placement and design of the VGs impact the aerodynamic characteristics of wing. The tests were carried out on a tapered swept-back wing at Re = 6.0×104 using counter-rotating vortex generators having Clark-Y airfoil at five different locations (x/c = 0.1, 0.2, 0.3, 0.4, and 0.5) and triangular VGs at the x/c = 0.1 location. A load cell is used to measure forces at angles of attack (AoA) ranging from 0° to 30°. It is observed that the maximum lift coefficient (CLmax) and aerodynamic performance of VGs having Clark-Y airfoil decrease when the position of the vortex generators changes from 0.1 to 0.5. The optimal results obtained from the study show that the tapered swept-back wing with the VGs having Clark-Y airfoil exhibits a significant increase of 37.5% in the CLmax and approximately 55% in the lift to drag ratio (L/D) at x/c = 0.1 compared with the baseline. At low AoA, the VGs having Clark-Y airfoil provided better lift, whereas at high AoA, the triangular VGs provided better lift. The drag coefficient of triangular VGs is higher than that of the baseline model and airfoil shaped VGs. This causes airfoil shaped VGs to have higher aerodynamic performance specifically at low AoA. This indicates that VGs having Clark-Y airfoil are effective in improving the aerodynamic performance of the wing.

Keywords

Vortex generators with Clark-Y airfoil, NACA0020, Tapered swept-back wing, Flow control

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