Bilecik Şeyh Edebali Üniversitesi Fen Bilimleri Dergisi

2458-7575

Bilecik Şeyh Edebali Üniversitesi

10.35193/bseufbd.588280

Engineering

Mühendislik

Flow Control around NACA 0015 Airfoil by Trailing Edge Flow Suction

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

https://orcid.org/0000-0001-5212-9170

Durhasan

Tahir

Adana Alparslan Türkeş Bilim ve Teknoloji Üniversitesi

09 30 2019

6 153 160 07 08 2019 09 05 2019

2014

Bilecik Şeyh Edebali Üniversitesi Fen Bilimleri Dergisi

In this study, the effect of flow suction attrailing edge on aerodynamic performance of NACA 0015 airfoil was investigated,numerically. Numerical solutions were performed by ANSYS Fluent using k-kL-ωtransition 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 comparedwith the base case. Laminar separationbubble was controlled significantly at low angles of attack. It was observedthat CL/CD increases up to 2.4 times CL/CDof the base case with the increasing suction ratio at α=2° ve 4°. On the other hand,it was observed that the CL/CDdid not alter significantly in comparison with the base case at α=8° since CD alsoincreases while CL increases.

Bu çalışmada,kanat firar kenarında uygulanan akış emme yönteminin NACA 0015 kanat profilininaerodinamik performansı üzerine etkileri sayısal çalışma ile araştırılmıştır.Sayısal çözümler Reynolds sayısının Re=48000 değerinde k-kL-ωtransition model kullanılarak ANSYS Fleunet tarafından gerçekleştirilmiştir. Üçfarklı 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 ilekıyaslanmıştır. Düşük hücum açılarında laminer ayrılma kabarcığı önemli ölçüdekontrol edilmiştir. Hücum açılarının α=2° ve 4° değerlerinde artan emme oranıile CL/CD oranının kontrolsüz durumun 2.4 katına kadararttığı gözlemlenmiştir. Ancak hücum açısının α=8° değerinde kaldırmakatsayısının artması ile birlikte sürüklenme katsayısının da artmasından dolayıCL/CD oranının kontrolsüz duruma göre önemli ölçüdeartmadığı gözlemlenmiştir.

Akış kontrolü Düşük Reynolds Sayılı Akış Kanat Profili Laminer ayrılma kabarcığı

Flow Control Low Reynolds Number Flow Airfoil Laminar Separation Bubble

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