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

Mehmet Seyhan; Aleyna Çolak; Mustafa Sarıoğlu

Makale detayları

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

Yazarlar:

Mehmet Seyhan | Aleyna Çolak | Mustafa Sarıoğlu

Yayıncı:

Nigde Omer Halisdemir University

Ana Başlıklar:

Aerodinamik (Hipersonik Aerodinamik Hariç)

Dergi:

Niğde Ömer Halisdemir Üniversitesi Mühendislik Bilimleri Dergisi Vol.13 Issue 3, pp.776-784

Belge Tipi:

Makale

Yayın Tarihi:

7/2024

Belge Dili:

İngilizce

Document ID (Org No.):

2001322963

pISSN:

2564-6605

Anahtar kelimeler:

Özet:

 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  6.0104 using counter-rotating vortex generators having Clark-Y airfoil at five different locations xc  0.1, 0.2, 0.3, 0.4, and 0.5 and triangular VGs at the xc  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 LD at xc  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.

 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  6.0104 using counter-rotating vortex generators having Clark-Y airfoil at five different locations xc  0.1, 0.2, 0.3, 0.4, and 0.5 and triangular VGs at the xc  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 LD at xc  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.

 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  6.0104 using counter-rotating vortex generators having Clark-Y airfoil at five different locations xc  0.1, 0.2, 0.3, 0.4, and 0.5 and triangular VGs at the xc  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 LD at xc  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.

 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, GÜlerin yerleşimi ve tasarımının kanadın aerodinamik özelliklerini nasıl etkilediğini anlamaktır. Testler, ters dönen aero-şekilli girdap üreteçleri xc  0.1, 0.2, 0.3, 0.4 ve 0.5 konumlarında, geleneksel girdap üreteçleri xc0.1 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 GÜlerin konumu xc0.1den 0.5e değişmesiyle CLmax değerinin ve bu değerin elde edildiği hücum açılarının düştüğü görülmektedir. Çalışmadan elde edilen optimal sonuçlar, Clark-Y uçak kanadı şekilli GÜlerin xc0.1 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 GÜler daha iyi taşıma sağlarken, yüksek hücum açılarında üçgensel GÜler daha iyi taşıma oluşturmuştur. Üçgensel GÜlerin sürükleme katsayısı düz modele ve uçak kanadı şekilli GÜlere göre daha yüksektir. Bu da uçak kanat şekilli GÜlerin aerodinamik performansının özellikle düşük açılarda daha yüksek olmasına neden olmaktadır. Bu durum Clark-Y kanat profiline sahip GÜlerin kanadın aerodinamik performansını artırmada etkili olduğunu göstermektedir.

Makale detayları

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

Yazarlar:

Mehmet Seyhan | Aleyna Çolak | Mustafa Sarıoğlu

Yayıncı:

Nigde Omer Halisdemir University

Ana Başlıklar:

Aerodinamik (Hipersonik Aerodinamik Hariç)

Dergi:

Niğde Ömer Halisdemir Üniversitesi Mühendislik Bilimleri Dergisi Vol.13 Issue 3, pp.776-784

Belge Tipi:

Makale

Yayın Tarihi:

7/2024

Belge Dili:

İngilizce

Document ID (Org No.):

2001322963

pISSN:

2564-6605

Vortex generators with Clark-Y airfoil

NACA0020

Tapered swept-back wing

Flow controlClark-Y şekilli girdap üreteci

NACA 0020

Konik geriye ok açılı kanat

Akış kontrol

Sayı

Makale detayları

Yazarlar: Mehmet Seyhan | Aleyna Çolak | Mustafa Sarıoğlu

Yayıncı: Nigde Omer Halisdemir University

Ana Başlıklar: Aerodinamik (Hipersonik Aerodinamik Hariç)

Dergi: Niğde Ömer Halisdemir Üniversitesi Mühendislik Bilimleri Dergisi Vol.13 Issue 3, pp.776-784

Belge Tipi: Makale

Yayın Tarihi: 7/2024

Belge Dili: İngilizce

Document ID (Org No.): 2001322963

pISSN: 2564-6605

Sayı

Yazarlar:

Mehmet Seyhan | Aleyna Çolak | Mustafa Sarıoğlu

Yayıncı:

Nigde Omer Halisdemir University

Ana Başlıklar:

Aerodinamik (Hipersonik Aerodinamik Hariç)

Dergi:

Niğde Ömer Halisdemir Üniversitesi Mühendislik Bilimleri Dergisi Vol.13 Issue 3, pp.776-784

Belge Tipi:

Makale

Yayın Tarihi:

7/2024

Belge Dili:

İngilizce

Document ID (Org No.):

2001322963

pISSN:

2564-6605