Politeknik Dergisi 2147-9429 Gazi Üniversitesi 10.2339/politeknik.1229081 Engineering Mühendislik NACA0009 ve NACA4415 Kanat Profillerinin Sayısal ve İstatistiksel Aerodinamik Performans Analizi Numerical and Statistical Aerodynamic Performance Analysis of NACA0009 and NACA4415 Airfoils https://orcid.org/0000-0002-7512-5997 Evran Savaş CANAKKALE ONSEKIZ MART UNIVERSITY https://orcid.org/0000-0002-9544-7336 Yıldır Salih Zeki ÇANAKKALE ONSEKİZ MART ÜNİVERSİTESİ, ÇANAKKALE UYGULAMALI BİLİMLER FAKÜLTESİ 07 25 2024 27 3 849 856 01 03 2023 01 16 2023 Copyright © 1998, Politeknik Dergisi 1998 Politeknik Dergisi

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.

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.

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