Politeknik Dergisi 2147-9429 Gazi Üniversitesi 10.2339/politeknik.391800 Engineering Mühendislik Modifiye Edilmiş NACA-0015 Kanat Yapısında Tüberkül Etkisinin Sayısal Analizi The Numeric Analysis of Tubercle Effect on Modified NACA-0015 Airfoil Tanürün Himmet Erdi Acır Adem 03 01 2019 22 1 185 195 11 04 2017 Copyright © 1998, Politeknik Dergisi 1998 Politeknik Dergisi

Bu çalışmada, kambur balinanınaerodinamik özellikleri, NACA-0015 kanat modeline uygulanarak kanat performansıincelenmiştir. Kambur balinanın avını takip etmesi ve yakalaması esnasındakimanevra kabiliyetinden ilham alınarak, NACA-0015 kanadının hücum kenarıbölgesine aynı dalga boyunda (w) ve farklı genlikteki (a) tüberkülleryerleştirilmiştir. Elde edilen 3 farklı modifiyeli NACA-0015 kanadı ile düzkanat, aerodinamik performans açısından karşılaştırılmıştır. Bu çalışmadakullanılan modifiye NACA-0015 kanatlarının dalga boyu değeri, chord(veter)  uzunluğunun %16’sı ve genliklerin değeri isesırasıyla chord uzunluğunun %0,05, %0,1 ve %0,15’i olarak belirlenmiştir. Kanatyapıları Solidwoks CAD programında tasarlanmıştır. ANSYS Fluent yazılımındaortalama Navier-Stokes analiz yönteminde k-epsilon realizable türbülansmodeliyle sayısal olarak analiz edilmiştir. Kanat açıklık oranı (en/boy oranı)değeri 1,1 seçilmiştir. 7,2x105 Reynolds sayısında, 0° ile 46°arasındaki hücum açılarında kanat üzerinde analizler yapılmıştır. Sonuçlarincelendiğinde, 0,05a0,16w (0,05a ve 0,16w) kanadın sürtünme katsayısı (CD)  düz kanatla kıyaslandığında %12,57 dahadüşüktür. İrtifa kaybı(Stall) sonrası hücum açıları için, 0,05a0,16w kanadı iledüz kanat ortalama kaldırma katsayısı (CL) ve CD değeriaçısından kıyaslandığında 0,5a0,16w kanadı sırasıyla %7,86 ve %9,79 daha yüksekdeğerlere sahiptir. Stall sonrasında aerodinamik verim(CL /CD),0,05a0,16w kanadının, düz kanattan %3,81 daha yüksek olduğu görülmektedir. 

In this study, the aerodynamic characteristics of thehumpback whale were investigated by applying the NACA-0015 model to the wing ofthe airfoil. Inspired by the maneuverability during the chase and capture ofthe humpback whale, NACA-0015 has placed the tubercles the same wavelength (w)and different amplitudes (a) in the leading edge region of the wing. The threedifferent modified wings and the baseline obtained were compared in terms ofaerodynamic performance. The wavelength of the modified wings used in thisstudy is 16% of the chord length and the values of the amplitudes weredetermined as 0,05%, 0,1% and 0,15%, respectively, of the chord length. Allwing structures were designed in Solidworks CAD program. These solid modelswere numerically analyzed with the k-epsilon realizable turbulence model in theaverage Navier-Stokes analysis method in ANSYS Fluent software. Wing opennessratio (aspect ratio) value 1,1 was selected. On the 7,2x105 Reynoldsnumber, analyzes were made on the wing at the attack angle between 0 ° and 46°. After the examination of the results, it’s found that the baseline has ahigher lift coefficient (CL) than the modified wing before thestall. The coefficient of friction (CD) of the 0,05a0,16w (0,05a ve0,16w) is 12,57% lower than that of the baseline. For post-stall angle ofattacks, when 0,05a0,16w wing is compared to baseline average CL andCD value, the wing of 0,5a0,16w has 7,86% and 9,79% higher valuesrespectively. After stall, It has seen that the aerodynamic efficiency (CL/ CD) of 0,05a0,16w is %3,81 higher than the baseline.  

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