AYAZ ÜMÜTLÜ, Hatice Cansu ;KIRAL, Zeki ;KARADENIZ, Ziya Haktan . Numerical and Experimental Investigation of Aspect Ratio Effect on Aerodynamic Performance of NACA 4415 Airfoil Section at Low Reynolds Number. Strojniški vestnik - Journal of Mechanical Engineering, [S.l.], v. 71, n.1-2, p. 51-57, january 2025. ISSN 0039-2480. Available at: <https://www.sv-jme.eu/sl/article/numerical-and-experimental-investigation-of-aspect-ratio-effect-on-aerodynamic-performance-of-naca-4415-airfoil-section-at-low-reynolds-number/>. Date accessed: 04 apr. 2025. doi:http://dx.doi.org/10.5545/sv-jme.2024.1155.
Ayaz Ümütlü, H., Kıral, Z., & Karadeniz, Z. (2025). Numerical and Experimental Investigation of Aspect Ratio Effect on Aerodynamic Performance of NACA 4415 Airfoil Section at Low Reynolds Number. Strojniški vestnik - Journal of Mechanical Engineering, 71(1-2), 51-57. doi:http://dx.doi.org/10.5545/sv-jme.2024.1155
@article{sv-jmesv-jme.2024.1155,
author = {Hatice Cansu Ayaz Ümütlü and Zeki Kıral and Ziya Haktan Karadeniz},
title = {Numerical and Experimental Investigation of Aspect Ratio Effect on Aerodynamic Performance of NACA 4415 Airfoil Section at Low Reynolds Number},
journal = {Strojniški vestnik - Journal of Mechanical Engineering},
volume = {71},
number = {1-2},
year = {2025},
keywords = {airfoil; wind tunnel; aspect ratio effect; aerodynamic coefficients; three-component balance; low Reynolds number; },
abstract = {In this study, the effect of aspect ratio on the aerodynamic coefficients is investigated for a NACA 4415 airfoil profile. Four different aspect ratios which are 3, 5, 7, and 9 are evaluated with the computational fluid dynamics (CFD) simulations and the experiments. The CFD studies are performed using a three-dimensional (3D) computational domain and by using the k–ω shear stress transport (SST) turbulence model for turbulence calculations. The measurements of the aerodynamic forces are carried out in open jet type wind tunnel using a three-component balance. CFD and experimental studies are performed at angles of attack from 0° to 25° and Reynolds number 85e3. The results show that as the aspect ratio increases, separation points move towards the leading edge of the airfoil and the stall angle reduces. Furthermore, it is observed that the lift coefficients increase with the increasing aspect ratio. The results obtained indicate that there is a harmony between the experimental data and the CFD solutions.},
issn = {0039-2480}, pages = {51-57}, doi = {10.5545/sv-jme.2024.1155},
url = {https://www.sv-jme.eu/sl/article/numerical-and-experimental-investigation-of-aspect-ratio-effect-on-aerodynamic-performance-of-naca-4415-airfoil-section-at-low-reynolds-number/}
}
Ayaz Ümütlü, H.,Kıral, Z.,Karadeniz, Z. 2025 January 71. Numerical and Experimental Investigation of Aspect Ratio Effect on Aerodynamic Performance of NACA 4415 Airfoil Section at Low Reynolds Number. Strojniški vestnik - Journal of Mechanical Engineering. [Online] 71:1-2
%A Ayaz Ümütlü, Hatice Cansu %A Kıral, Zeki %A Karadeniz, Ziya Haktan %D 2025 %T Numerical and Experimental Investigation of Aspect Ratio Effect on Aerodynamic Performance of NACA 4415 Airfoil Section at Low Reynolds Number %B 2025 %9 airfoil; wind tunnel; aspect ratio effect; aerodynamic coefficients; three-component balance; low Reynolds number; %! Numerical and Experimental Investigation of Aspect Ratio Effect on Aerodynamic Performance of NACA 4415 Airfoil Section at Low Reynolds Number %K airfoil; wind tunnel; aspect ratio effect; aerodynamic coefficients; three-component balance; low Reynolds number; %X In this study, the effect of aspect ratio on the aerodynamic coefficients is investigated for a NACA 4415 airfoil profile. Four different aspect ratios which are 3, 5, 7, and 9 are evaluated with the computational fluid dynamics (CFD) simulations and the experiments. The CFD studies are performed using a three-dimensional (3D) computational domain and by using the k–ω shear stress transport (SST) turbulence model for turbulence calculations. The measurements of the aerodynamic forces are carried out in open jet type wind tunnel using a three-component balance. CFD and experimental studies are performed at angles of attack from 0° to 25° and Reynolds number 85e3. The results show that as the aspect ratio increases, separation points move towards the leading edge of the airfoil and the stall angle reduces. Furthermore, it is observed that the lift coefficients increase with the increasing aspect ratio. The results obtained indicate that there is a harmony between the experimental data and the CFD solutions. %U https://www.sv-jme.eu/sl/article/numerical-and-experimental-investigation-of-aspect-ratio-effect-on-aerodynamic-performance-of-naca-4415-airfoil-section-at-low-reynolds-number/ %0 Journal Article %R 10.5545/sv-jme.2024.1155 %& 51 %P 7 %J Strojniški vestnik - Journal of Mechanical Engineering %V 71 %N 1-2 %@ 0039-2480 %8 2025-01-06 %7 2025-01-06
Ayaz Ümütlü, Hatice Cansu, Zeki Kıral, & Ziya Haktan Karadeniz. "Numerical and Experimental Investigation of Aspect Ratio Effect on Aerodynamic Performance of NACA 4415 Airfoil Section at Low Reynolds Number." Strojniški vestnik - Journal of Mechanical Engineering [Online], 71.1-2 (2025): 51-57. Web. 04 Apr. 2025
TY - JOUR AU - Ayaz Ümütlü, Hatice Cansu AU - Kıral, Zeki AU - Karadeniz, Ziya Haktan PY - 2025 TI - Numerical and Experimental Investigation of Aspect Ratio Effect on Aerodynamic Performance of NACA 4415 Airfoil Section at Low Reynolds Number JF - Strojniški vestnik - Journal of Mechanical Engineering DO - 10.5545/sv-jme.2024.1155 KW - airfoil; wind tunnel; aspect ratio effect; aerodynamic coefficients; three-component balance; low Reynolds number; N2 - In this study, the effect of aspect ratio on the aerodynamic coefficients is investigated for a NACA 4415 airfoil profile. Four different aspect ratios which are 3, 5, 7, and 9 are evaluated with the computational fluid dynamics (CFD) simulations and the experiments. The CFD studies are performed using a three-dimensional (3D) computational domain and by using the k–ω shear stress transport (SST) turbulence model for turbulence calculations. The measurements of the aerodynamic forces are carried out in open jet type wind tunnel using a three-component balance. CFD and experimental studies are performed at angles of attack from 0° to 25° and Reynolds number 85e3. The results show that as the aspect ratio increases, separation points move towards the leading edge of the airfoil and the stall angle reduces. Furthermore, it is observed that the lift coefficients increase with the increasing aspect ratio. The results obtained indicate that there is a harmony between the experimental data and the CFD solutions. UR - https://www.sv-jme.eu/sl/article/numerical-and-experimental-investigation-of-aspect-ratio-effect-on-aerodynamic-performance-of-naca-4415-airfoil-section-at-low-reynolds-number/
@article{{sv-jme}{sv-jme.2024.1155},
author = {Ayaz Ümütlü, H., Kıral, Z., Karadeniz, Z.},
title = {Numerical and Experimental Investigation of Aspect Ratio Effect on Aerodynamic Performance of NACA 4415 Airfoil Section at Low Reynolds Number},
journal = {Strojniški vestnik - Journal of Mechanical Engineering},
volume = {71},
number = {1-2},
year = {2025},
doi = {10.5545/sv-jme.2024.1155},
url = {https://www.sv-jme.eu/sl/article/numerical-and-experimental-investigation-of-aspect-ratio-effect-on-aerodynamic-performance-of-naca-4415-airfoil-section-at-low-reynolds-number/}
}
TY - JOUR AU - Ayaz Ümütlü, Hatice Cansu AU - Kıral, Zeki AU - Karadeniz, Ziya Haktan PY - 2025/01/06 TI - Numerical and Experimental Investigation of Aspect Ratio Effect on Aerodynamic Performance of NACA 4415 Airfoil Section at Low Reynolds Number JF - Strojniški vestnik - Journal of Mechanical Engineering; Vol 71, No 1-2 (2025): Strojniški vestnik - Journal of Mechanical Engineering DO - 10.5545/sv-jme.2024.1155 KW - airfoil, wind tunnel, aspect ratio effect, aerodynamic coefficients, three-component balance, low Reynolds number, N2 - In this study, the effect of aspect ratio on the aerodynamic coefficients is investigated for a NACA 4415 airfoil profile. Four different aspect ratios which are 3, 5, 7, and 9 are evaluated with the computational fluid dynamics (CFD) simulations and the experiments. The CFD studies are performed using a three-dimensional (3D) computational domain and by using the k–ω shear stress transport (SST) turbulence model for turbulence calculations. The measurements of the aerodynamic forces are carried out in open jet type wind tunnel using a three-component balance. CFD and experimental studies are performed at angles of attack from 0° to 25° and Reynolds number 85e3. The results show that as the aspect ratio increases, separation points move towards the leading edge of the airfoil and the stall angle reduces. Furthermore, it is observed that the lift coefficients increase with the increasing aspect ratio. The results obtained indicate that there is a harmony between the experimental data and the CFD solutions. UR - https://www.sv-jme.eu/sl/article/numerical-and-experimental-investigation-of-aspect-ratio-effect-on-aerodynamic-performance-of-naca-4415-airfoil-section-at-low-reynolds-number/
Ayaz Ümütlü, Hatice Cansu, Kıral, Zeki, AND Karadeniz, Ziya Haktan. "Numerical and Experimental Investigation of Aspect Ratio Effect on Aerodynamic Performance of NACA 4415 Airfoil Section at Low Reynolds Number" Strojniški vestnik - Journal of Mechanical Engineering [Online], Volume 71 Number 1-2 (06 January 2025)
Strojniški vestnik - Journal of Mechanical Engineering 71(2025)1-2, 51-57
© The Authors 2025. CC BY 4.0 Int.
In this study, the effect of aspect ratio on the aerodynamic coefficients is investigated for a NACA 4415 airfoil profile. Four different aspect ratios which are 3, 5, 7, and 9 are evaluated with the computational fluid dynamics (CFD) simulations and the experiments. The CFD studies are performed using a three-dimensional (3D) computational domain and by using the k–ω shear stress transport (SST) turbulence model for turbulence calculations. The measurements of the aerodynamic forces are carried out in open jet type wind tunnel using a three-component balance. CFD and experimental studies are performed at angles of attack from 0° to 25° and Reynolds number 85e3. The results show that as the aspect ratio increases, separation points move towards the leading edge of the airfoil and the stall angle reduces. Furthermore, it is observed that the lift coefficients increase with the increasing aspect ratio. The results obtained indicate that there is a harmony between the experimental data and the CFD solutions.