Değiştirilmiş Bir Naca Kanat Geometrisinin Akış ve Mekanik Özellikleri

Yıl 2021, , 815 - 825, 30.09.2021

Mustafa Murat Yavuz

https://doi.org/10.21605/cukurovaumfd.1005807

Öz

Uçma yeteneği doğrudan kanat geometrisinin yapısı ile ilgilidir. Kanat yapısı her çalışma koşuluna göre farklı tasarlanmaktadır. Bu çalışmada, serbest biçimli bir kanat profili kesiti tasarlanmış ve modelin akış etkisi altındaki davranışı dalış ve kalkış açıları açısından incelenmiştir. Analizde hesaplamalı akışkanlar dinamiği yöntemi kullanılmıştır. Yöntemin duyarlılığı, bir NACA kanat profili kesitinin çözümü literatürdeki deneysel sonuçlarla karşılaştırılarak kontrol edilmiş ve çalışmada kullanılabilirliği kabul edilmiştir. Ayrıca çalışmada kanat geometrisi 3 boyutlu ve katmanlı olarak modellenmiş ve mekanik özellikleri incelenmiştir. Tasarlanan kanat profili, kaldırma yönünde daha baskın akış yapısına sahiptir. Simetrik olmayan kanat profili, simetrik olmayan Cl-Cd dağılımına neden olur. Kanat yapısının kaldırmada daha baskın olması sonucunda, pozitif hücum açısının deformasyon ve gerilme sonuçları negatif sonuçlara göre daha fazla olduğu gözlemlendi. Hücum açısına bağlı olarak kanat üzerindeki basınç ve akış etkileri daha yüksek eğilme-burulma etkisine neden olmuş ve kanadın sabitleme bölgesinde gerilmeleri arttırmıştır. En düşük deformasyon ve ortalama gerilmeler -4° hücum açısında meydana gelmiştir. Sonuçlar akış ve mekanik bulgular neticesinde tartışılmıştır

Anahtar Kelimeler

Hücum açısı, HAD, Deformasyon, Yapısal analiz

Flow and Mechanical Characteristics of a Modified Naca Wing Geometry

Öz

The flying ability is directly related to the structure of the wing geometry. The wing structure is designed differently according to each working conditions. In this study, a free-formed airfoil section was designed and the behaviour of the model under the influence of flow was investigated in terms of diving and takeoff angles. Computational fluid dynamics method was used in the analysis. The sensitivity of the method was checked by comparing the solution of a NACA airfoil section with the experimental results in the literature and its usability in the study was accepted. Also, in the study, the wing geometry was modelled as 3D and layered, and its mechanical properties were examined. The designed airfoil has more dominant
flow structure in the lift direction. Non-symmetrical airfoil causes unsymmetrical Cl-Cd distribution. As a result of the wing structure being more dominant in lift, it was observed that the deformation and stress results of the positive angle of attack were higher than the negative results. Depending on the angle of attack, the pressure and flow effects on the wing caused a higher bending-torsion effect and increased the stresses in the fixation region of the wing. The lowest deformation and average stresses occurred at -4° angle of attack. The results are discussed as a result of flow and mechanical findings.

Anahtar Kelimeler

Angle of attack, CFD, Deformation, Structural analysis

Kaynakça

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