Flow Control around NACA 0015 Airfoil by Trailing Edge Flow Suction

Yıl 2019, , 153 - 160, 30.09.2019

Tahir Durhasan

https://doi.org/10.35193/bseufbd.588280

Cited By: 2

Öz

In this study, the effect of flow suction at
trailing edge on aerodynamic performance of NACA 0015 airfoil was investigated,
numerically. Numerical solutions were performed by ANSYS Fluent using k-k_L-ω
transition model at Reynolds number of Re=48000. Three different suction ratios
(θ=0.05, 0.1 ve 0.2) were tested at four different angles of attacks (α=2°, 4°, 6° ve 8°) and obtained results were compared
with the base case.  Laminar separation
bubble was controlled significantly at low angles of attack. It was observed
that C_L/C_D increases up to 2.4 times C_L/C_D
of the base case with the increasing suction ratio at α=2° ve 4°. On the other hand,
it was observed that the C_L/C_D
did not alter significantly in comparison with the base case at α=8° since C_D also
increases while C_L increases.  

Anahtar Kelimeler

Flow Control, Low Reynolds Number Flow, Airfoil, Laminar Separation Bubble

NACA 0015 Kanat Profilinin Etrafındaki Akışın Firar Kenarından Akış Emme ile Kontrol Edilmesi

Öz

Bu çalışmada,
kanat firar kenarında uygulanan akış emme yönteminin NACA 0015 kanat profilinin
aerodinamik performansı üzerine etkileri sayısal çalışma ile araştırılmıştır.
Sayısal çözümler Reynolds sayısının Re=48000 değerinde k-k_L-ω
transition model kullanılarak ANSYS Fleunet tarafından gerçekleştirilmiştir. Üç
farklı emme oranı (θ=0.05, 0.1 ve 0.2) dört farklı kanat hücum açısında (α=2°,
4°, 6° ve 8°) test edilmiştir ve elde edilen bulgular kontrolsüz durum ile
kıyaslanmıştır. Düşük hücum açılarında laminer ayrılma kabarcığı önemli ölçüde
kontrol edilmiştir. Hücum açılarının α=2° ve 4° değerlerinde artan emme oranı
ile C_L/C_D oranının kontrolsüz durumun 2.4 katına kadar
arttığı gözlemlenmiştir. Ancak hücum açısının α=8° değerinde kaldırma
katsayısının artması ile birlikte sürüklenme katsayısının da artmasından dolayı
C_L/C_D oranının kontrolsüz duruma göre önemli ölçüde
artmadığı gözlemlenmiştir.

Anahtar Kelimeler

Akış kontrolü, Düşük Reynolds Sayılı Akış, Kanat Profili, Laminer ayrılma kabarcığı

Kaynakça

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