An experimental study on aerodynamics of NACA2415 aerofoil at low Re numbers

Genç, Mustafa Serdar; Karasu, İlyas; Açıkel, Halil Hakan

doi:10.1016/j.expthermflusci.2012.01.029

Cited by 99 publications

(56 citation statements)

References 25 publications

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“…The wind tunnel is a low-speed suction type and it has 50 cm x 50 cm test section with a transparent plexiglass wall for visualization processes. It has a low free stream turbulence intensity in which it is demonstrated 0.3% at maximum speed (40 m/s) and 0.7% at minimum speed (5 m/s) [5].…”

Section: Wind Tunnel and Flow Conditionsmentioning

confidence: 99%

“…Thus, new opportunities for innovation have been occurred to obtain the value of wind energy such as clean resource and low cost. Either different airfoil models [1] were searched or flow phenomenon over the airfoil operating at low Reynolds number such as laminar separation bubble (LSB), flow separation, transition [2][3][4][5][6][7] were studied. It was concluded that the LSB negatively exhibited major role on aerodynamic performance.…”

Section: Introductionmentioning

confidence: 99%

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Rüzgar Türbini Kanadı Üzerindeki Yüzey Pürüzlülüğü Etkisinin Deneysel İncelenmesi

Koca¹,

Genç²,

Açıkel³

2016

Çukurova Üniversitesi Mühendislik-Mimarlık Fakültesi Dergisi

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The present study ensures an experimental investigation of NACA4412 wind turbine blade airfoil prepared with the sandpaper as a roughness device in order to control its flow. The smoke-wire and hotwire experiments were carried out at low Reynolds number ranging from 25000 to 75000 and angle of attack of 8°. As geometrical parameters, height of sandpaper and it location over the airfoil were conducted. It was positioned 15%-25% chord length. Height of sandpaper was selected 0.5 mm. The experimental results revealed that the flow over NACA4412 was affected when sandpaper was utilized because either amount of lift apparently increased or the location and size of laminar separation bubble (LSB) were changed. As a result, it was shown that the use of sandpaper provided passive flow control and it was an effective way in terms of delay or suppress separation over NACA4412 airfoil.Keywords: Low reynolds number, Laminar separation bubble, Surface roughness, Passive flow control Rüzgar Türbini Kanadı Üzerindeki Yüzey Pürüzlülüğü Etkisinin Deneysel İncelenmesi ÖzMevcut çalışma, akış kontrolü sağlamak için pürüzlülük elemanı olan zımpara kağıdı ile hazırlanmış NACA4412 rüzgar türbini kanadının deneysel çalışmasını sağlamaktadır. Duman teli ve Sıcak-tel anemometresi deneyleri 8° hücum açısında ve 25000 ile 75000 arasında değişen hücum açılarında gerçekleştirilmiştir. Geometrik parametre olarak, kanat üzerindeki pürüzlülüğün yeri ve yüksekliği ele alınmıştır. Pürüzlülük %15-25 kord boyuna yerleştirilmiştir. Zımpara kağıdı yüksekliği 0,5 mm olarak seçilmiştir. Önceden deneysel çalışmalar NACA4412 kanat profilinin aerodinamik performansı açısından iyi sonuçlar gösterecek mi şeklinde düşünülmüştü. Gerçekten, deneysel sonuçlar zımpara kağıdı kullanıldığı zaman NACA4412 kanat profili üzerindeki akışın etkilendiğini ortaya çıkardı, çünkü ya kanadın kaldırma miktarında belli bir artış vardı ya da laminer ayrılma kabarcığının konumu değiştirilmişti. Sonuç olarak, zımparanın kullanılması pasif akış kontrolü sağladığını ve NACA4412 kanat profili üzerindeki akış ayrılmasını ertelediği ya da yok ettiğini göstermektedir.

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Section: Wind Tunnel and Flow Conditionsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Rüzgar Türbini Kanadı Üzerindeki Yüzey Pürüzlülüğü Etkisinin Deneysel İncelenmesi

Koca¹,

Genç²,

Açıkel³

2016

Çukurova Üniversitesi Mühendislik-Mimarlık Fakültesi Dergisi

Self Cite

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“…Viscous effects, separated and vortical flows are more prevalent and separation bubbles, transition, and reattachment processes are very attractive and also little understood at low Re number aerodynamics [1]. At low Reynolds number flow conditions, some negative effects are occurred such as decreasing on lift, increasing on drag, reducing stability of the aircraft, vibration, and noise due to the laminar separation bubble [4][5][6][7][8][9][10][11]. Genç et al conducted an experimental [9] and numerical [11] studies over the NACA2415 aerofoil at various angles of attack and low Reynolds numbers.…”

Section: Introductionmentioning

confidence: 99%

“…At low Reynolds number flow conditions, some negative effects are occurred such as decreasing on lift, increasing on drag, reducing stability of the aircraft, vibration, and noise due to the laminar separation bubble [4][5][6][7][8][9][10][11]. Genç et al conducted an experimental [9] and numerical [11] studies over the NACA2415 aerofoil at various angles of attack and low Reynolds numbers. They noticed that due to the increasing Reynolds number and angle of attack the point of separation and reattachment moved towards to leading edge.…”

Section: Introductionmentioning

confidence: 99%

“…The aerodynamic of low aspect-ratio wings have been extensively investigated by aerodynamic researches keen on low aspect ratio wings and low Reynolds numbers [1][2][3][4][5][6][7][8][9][10][11][12][13][14][15][16][17][18][19]. Viscous effects, separated and vortical flows are more prevalent and separation bubbles, transition, and reattachment processes are very attractive and also little understood at low Re number aerodynamics [1].…”

Section: Introductionmentioning

confidence: 99%

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Effect of tip vortices on flow over NACA4412 aerofoil with different aspect ratios

Genç

Özkan

Açıkel

et al. 2016

EPJ Web of Conferences

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Abstract. Effect of tip vortices on flow and laminar separation bubble over NACA4412 aerofoil at low Reynolds numbers and different angles of attack was investigated in detail by performing force and flow visualization via smoke wire technique. Experiments have been done at Reynolds number of 50000 and the wing model of aspect-ratio was 1 and 3, respectively. From the experimental results, the flow visualization results showed that tip vortices effect on the laminar separation bubble and the bubble reduces over the wing with low aspect ratio as the angle of attack increased. Moreover, it was noticed that stall angles decreased as aspect-ratio increased at the same Reynolds number.

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