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. Articles in Press, [S.l.], v. 0, n.0, p. , 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: 19 jan. 2025. doi:http://dx.doi.org/.
Ayaz Ümütlü, H., Kıral, Z., & Karadeniz, Z. (0). Numerical and Experimental Investigation of Aspect Ratio Effect on Aerodynamic Performance of NACA 4415 Airfoil Section at Low Reynolds Number. Articles in Press, 0(0), . doi:http://dx.doi.org/
@article{.,
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 = {Articles in Press},
volume = {0},
number = {0},
year = {0},
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 CFD simulations and the experiments. The CFD studies are performed using a 3D computational domain and by using the k-ω SST turbulence model for turbulence calculations. The measurements of the aerodynamic forces are carried out using open jet type wind tunnel. 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. It is seen that the CFD solutions and the experimental data are in good agreement according to obtained results.},
issn = {0039-2480}, pages = {}, doi = {},
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/}
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Ayaz Ümütlü, H.,Kıral, Z.,Karadeniz, Z. 0 January 0. Numerical and Experimental Investigation of Aspect Ratio Effect on Aerodynamic Performance of NACA 4415 Airfoil Section at Low Reynolds Number. Articles in Press. [Online] 0:0
%A Ayaz Ümütlü, Hatice Cansu %A Kıral, Zeki %A Karadeniz, Ziya Haktan %D 0 %T Numerical and Experimental Investigation of Aspect Ratio Effect on Aerodynamic Performance of NACA 4415 Airfoil Section at Low Reynolds Number %B 0 %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 CFD simulations and the experiments. The CFD studies are performed using a 3D computational domain and by using the k-ω SST turbulence model for turbulence calculations. The measurements of the aerodynamic forces are carried out using open jet type wind tunnel. 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. It is seen that the CFD solutions and the experimental data are in good agreement according to obtained results. %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 %& %P 1 %J Articles in Press %V 0 %N 0 %@ 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." Articles in Press [Online], 0.0 (0): . Web. 19 Jan. 2025
TY - JOUR AU - Ayaz Ümütlü, Hatice Cansu AU - Kıral, Zeki AU - Karadeniz, Ziya Haktan PY - 0 TI - Numerical and Experimental Investigation of Aspect Ratio Effect on Aerodynamic Performance of NACA 4415 Airfoil Section at Low Reynolds Number JF - Articles in Press DO - 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 CFD simulations and the experiments. The CFD studies are performed using a 3D computational domain and by using the k-ω SST turbulence model for turbulence calculations. The measurements of the aerodynamic forces are carried out using open jet type wind tunnel. 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. It is seen that the CFD solutions and the experimental data are in good agreement according to obtained results. 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/
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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 = {Articles in Press},
volume = {0},
number = {0},
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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/}
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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 - Articles in Press; Vol 0, No 0 (0): Articles in Press DO - 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 CFD simulations and the experiments. The CFD studies are performed using a 3D computational domain and by using the k-ω SST turbulence model for turbulence calculations. The measurements of the aerodynamic forces are carried out using open jet type wind tunnel. 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. It is seen that the CFD solutions and the experimental data are in good agreement according to obtained results. 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" Articles in Press [Online], Volume 0 Number 0 (06 January 2025)
Articles in Press
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 CFD simulations and the experiments. The CFD studies are performed using a 3D computational domain and by using the k-ω SST turbulence model for turbulence calculations. The measurements of the aerodynamic forces are carried out using open jet type wind tunnel. 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. It is seen that the CFD solutions and the experimental data are in good agreement according to obtained results.