Modifiye Edilmiş NACA-0015 Kanat Yapısında Tüberkül Etkisinin Sayısal Analizi

Bu çalışmada, kambur balinanın aerodinamik özellikleri, NACA-0015 kanat modeline uygulanarak kanat performansı incelenmiştir. Kambur balinanın avını takip etmesi ve yakalaması esnasındaki manevra kabiliyetinden ilham alınarak, NACA-0015 kanadının hücum kenarı bölgesine aynı dalga boyunda (w) ve farklı genlikteki (a) tüberküller yerleştirilmiştir. Elde edilen 3 farklı modifiyeli NACA-0015 kanadı ile düz kanat, aerodinamik performans açısından karşılaştırılmıştır. Bu çalışmada kullanılan modifiye NACA-0015 kanatlarının dalga boyu değeri, chord(veter) uzunluğunun %16’sı ve genliklerin değeri ise sırasıyla chord uzunluğunun %0,05, %0,1 ve %0,15’i olarak belirlenmiştir. Kanat yapıları Solidwoks CAD programında tasarlanmıştır. ANSYS Fluent yazılımında ortalama Navier-Stokes analiz yönteminde k-epsilon realizable türbülans modeliyle 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. Sonuçlar incelendiğinde, 0,05a0,16w (0,05a ve 0,16w) kanadın sürtünme katsayısı (CD) düz kanatla kıyaslandığında %12,57 daha düşüktür. İrtifa kaybı(Stall) sonrası hücum açıları için, 0,05a0,16w kanadı ile düz kanat ortalama kaldırma katsayısı (CL) ve CD değeri açısından kıyaslandığında 0,5a0,16w kanadı sırasıyla %7,86 ve %9,79 daha yüksek değerlere sahiptir. Stall sonrasında aerodinamik verim(CL /CD), 0,05a0,16w kanadının, düz kanattan %3,81 daha yüksek olduğu görülmektedir.

Anahtar Kelimeler:

Kambur balina, uçak kanadı, aerodinamik, tüberkül, hesaplamalı akışkanlar dinamiği

The Numeric Analysis of Tubercle Effect on Modified NACA-0015 Airfoil

In this study, the aerodynamic characteristics of the humpback whale were investigated by applying the NACA-0015 model to the wing of the airfoil. Inspired by the maneuverability during the chase and capture of the 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 three different modified wings and the baseline obtained were compared in terms of aerodynamic performance. The wavelength of the modified wings used in this study is 16% of the chord length and the values of the amplitudes were determined as 0,05%, 0,1% and 0,15%, respectively, of the chord length. All wing structures were designed in Solidworks CAD program. These solid models were numerically analyzed with the k-epsilon realizable turbulence model in the average Navier-Stokes analysis method in ANSYS Fluent software. Wing openness ratio (aspect ratio) value 1,1 was selected. On the 7,2x105 Reynolds number, 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 a higher lift coefficient (CL) than the modified wing before the stall. The coefficient of friction (CD) of the 0,05a0,16w (0,05a ve 0,16w) is 12,57% lower than that of the baseline. For post-stall angle of attacks, when 0,05a0,16w wing is compared to baseline average CL and CD value, the wing of 0,5a0,16w has 7,86% and 9,79% higher values respectively. After stall, It has seen that the aerodynamic efficiency (CL / CD) of 0,05a0,16w is %3,81 higher than the baseline.

Keywords:

Humpback whale, airfoil, aerodynamic, tubercle, computational fluid dynamics,

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