NACA 0015 kanat profilinin düşük Reynolds sayılarında aerodinamik performans analizi

Year 2025, Volume: 5 Issue: 1, 65 - 85, 28.02.2025

Mustafa Buğday

https://doi.org/10.52995/jass.1619615

Abstract

Bu çalışma, NACA 0015 serisi simetrik bir kanat profilinin aerodinamik performansını artırmayı amaçlamaktadır. Araştırma, Ansys Fluid Flow (CFD) modülü kullanılarak yürütülmüştür. Analiz alanı 300.000 mesh elemandan oluşmaktadır. Birkaç karşılaştırmalı analiz, düşük Reynolds sayılarında ve α=-100 ile 100 arasında değişen hücum açılarında gerçekleştirilmiştir. Hücum açısındaki bir artış genellikle aerodinamik kuvvet katsayılarında (Cl, Cd ve Cl/Cd) bir yükselmeye yol açmıştır. Çalışmamızda, literatürdeki benzer çalışmalarla karşılaştırıldığında, Spalart-Allmaras türbülans modeli ve Re=1×106 kullanılarak α=800'de optimum değerlere ulaşılmıştır. Başlangıç koşuluna göre kaldırma katsayısında (Cl) %30'luk bir artış elde edilmiştir. Ayrıca kanat profilinin alt ve üst yüzeyleri arasındaki basınç farkından dolayı kaydedilen ortalama hız değerleri sırasıyla 29,6 m/s ve 18,1 m/s olmuştur. Bu bulgularla tutarlı olarak, özellikle rüzgâr türbinlerinde tercih edilen bu serinin, deneysel ortamlardan elde edilen test verileriyle gelecekte daha verimli ve etkili çalışabileceği düşünülmektedir.

Keywords

Kanat profili, NACA 0015, Ansys, CFD

Aerodynamic performance analysis of NACA 0015 airfoil at low Reynolds numbers

Abstract

This study aims to enhance the aerodynamic performance of a NACA 0015 series symmetric airfoil. The research was conducted using the Ansys Fluid Flow (CFD) module. The analysis area comprised 300,000 mesh elements. Several comparative analyses were conducted at low Reynold number (Re) and angles of attack ranging from α=-100 to 100. An increase in the angle of attack typically led to an elevation in the aerodynamic force coefficients (Cl, Cd, and Cl/Cd). In our study, the optimal values were attained at α=80, utilizing the Spalart-Allmaras turbulence model and Re=1×106, in comparison with analogous studies in literature. A 30% increase in lift coefficient (Cl) was attained relative to the initial condition. Furthermore, owing to the pressure differential between the lower and upper surfaces of the wing profile, the average velocity values recorded were 29.6 m/s and 18.1 m/s, respectively. Consistent with these findings, it is believed that this series, particularly favored in wind turbines, may operate more efficiently and effectively in the future with the test data acquired from experimental settings.

Keywords

Airfoil, NACA 0015, Ansys, CFD

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