NACA0009 ve NACA4415 Kanat Profillerinin Sayısal ve İstatistiksel Aerodinamik Performans Analizi

Öz

Bu sayısal ve istatistiksel çalışmada, NACA-0009 ve NACA-4415 profillerinin kaldırma ve sürükleme katsayısı performansları, sabit rüzgar hızında çeşitli hücum açılarına göre değerlendirilmiştir. Kanat profillerinin kaldırma ve sürükleme katsayıları, hesaplamalı akışkanlar dinamiği kodu ANSYS FLUENT ile sayısal olarak belirlendi. Sayısal hesaplamaların analiz tasarımı, Taguchi yöntemine dayalı L16 ortogonal dizisi kullanılarak gerçekleştirilmiştir. Hücum açıları ve kanat tipleri kontrol faktörleri olarak kabul edildi. Her kontrol faktörünün tepkiler üzerindeki optimum seviyesi ve etkisi, Sinyal-Gürültü oranı ve varyans analizleri kullanılarak istatistiksel olarak uygulandı. Bu çalışma sonucunda NACA0009 kanat profiline kıyasla NACA4415 kanat profili kullanılarak maksimum kaldırma ve minimum sürükleme katsayısı elde edilmiştir. Hücum açısının artması, her iki kanat profili için kaldırma ve sürükleme katsayılarının artmasına neden olur.

Anahtar Kelimeler

• Hücum açısı
• kanat profili
• CFD
• Taguchi yöntemi
• aerodinamik
• airfoil
• Taguchi method
• aerodynamic

Proje Numarası

1919B012200301

Numerical and Statistical Aerodynamic Performance Analysis of NACA0009 and NACA4415 Airfoils

Öz

In this numerical and statistical study, lift and drag coefficient performances of NACA-0009 and NACA-4415 airfoils were evaluated in accordance with various attack angle at constant velocity of wind. Lift and drag coefficients of airfoils was numerically determined by computational fluid dynamics code ANSYS FLUENT. Analysis design of numerical calculations was implemented using L16 orthogonal array based on Taguchi method. Angles of attack and airfoil types were considered as control factors. The optimum level and effect of each control factor on responses was statistically implemented using analyses of Signal-to-Noise ratio and variance. As a result of this study, maximum lift and minimum drag coefficient were achieved by using NACA4415 airfoil compared to NACA0009 airfoil. The increase of the angle of attack leads to the increase on the lift and drag coefficients for both airfoils.  

Anahtar Kelimeler

• Angle of attack
• airfoil
• CFD
• Taguchi method
• aerodynamic

Destekleyen Kurum

The research was supported financially by the Scientific and Technological Research Council of Turkey (TÜBİTAK-2209A)

Proje Numarası

1919B012200301

Kaynakça

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