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Numerical investigation on the pressure drag of some low-speed airfoils for UAV application

Progressive advancements in small to medium-sized fixed-wing UAVs call for prototype designing to be fast, accurate, and economical. This requires the numerical assessment of airfoil performance to be based on high fidelity replication of wind tunnel data. Furthermore, integration of drag reducti...

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Main Authors: Zohary, Aideal Czar, Asrar, Waqar, Mohammed Aldheeb, Mohammed Abdulmalek
Format: Article
Language:English
English
Published: ISSR 2021
Subjects:
TL500 Aeronautics
Online Access:http://irep.iium.edu.my/89039/7/89309_Numerical%20investigation%20on%20the%20pressure%20drag%20of%20some%20low-speed%20airfoils%20for%20UAV%20application_SCOPUS.pdf
http://irep.iium.edu.my/89039/13/89309_Numerical%20investigation%20on%20the%20pressure%20drag%20of%20some%20low-speed%20airfoils%20for%20UAV%20application.pdf
http://irep.iium.edu.my/89039/
http://akademiabaru.com/submit/index.php/cfdl/article/view/3075/2660
https://doi.org/10.37934/cfdl.13.2.2948
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spelling my.iium.irep.890392021-04-04T12:43:54Z http://irep.iium.edu.my/89039/ Numerical investigation on the pressure drag of some low-speed airfoils for UAV application Zohary, Aideal Czar Asrar, Waqar Mohammed Aldheeb, Mohammed Abdulmalek TL500 Aeronautics Progressive advancements in small to medium-sized fixed-wing UAVs call for prototype designing to be fast, accurate, and economical. This requires the numerical assessment of airfoil performance to be based on high fidelity replication of wind tunnel data. Furthermore, integration of drag reduction techniques is attractive as improvements in endurance, payload capacity and reduction in carbon footprints can be attained. Since a variety of suitable airfoil geometries are currently available for this application, selecting a fitting candidate can be difficult therefore risking potential gain in efficiency. The aim of this paper is to assist in resolving this issue by investigating the variation in pressure drag and its distribution with respect to the type of airfoil geometry, angle of attack, and the contribution of pressure towards the total drag at low Reynolds numbers. The airfoils selected in this study comprises of the NACA 4415, FX 61-184, E420 and S1223 which are preferred for subsonic UAV applications in addition to having the NACA 0012 serving as a standard profile. Performance of the S1223 airfoil was examined at a chord-based Reynolds number of 0.3 x 106 with the remaining airfoils at 1.0 x 106 for a range of angle of attack of around 0-10°. The unsteady 3-equation Intermittency SST model from ANSYS FLUENT 2020 was utilized with gradual reduction of timestep from 0.001s, 0.0005s, 0.00025s and 0.0001s. Experimental lift and drag validation across the airfoils generally suggest that the transitional model regularly outperforms XFOIL. Among the selection, concave airfoils such as the E420 and S1223 excel in delivering high lift at the expense of an increase in drag. Evaluation of the l/d ratio alone may underestimate their potential. Hence, further studies should focus on the implementation of drag reduction techniques on concave airfoils to enhance their performance. At the maximum tested angle of attack, the E420 reaches a cl value of 2.09 and S1223 at 1.98 while the FX 61-184 only at 1.57 and NACA 4415 at 1.36. ISSR 2021-02-27 Article PeerReviewed application/pdf en http://irep.iium.edu.my/89039/7/89309_Numerical%20investigation%20on%20the%20pressure%20drag%20of%20some%20low-speed%20airfoils%20for%20UAV%20application_SCOPUS.pdf application/pdf en http://irep.iium.edu.my/89039/13/89309_Numerical%20investigation%20on%20the%20pressure%20drag%20of%20some%20low-speed%20airfoils%20for%20UAV%20application.pdf Zohary, Aideal Czar and Asrar, Waqar and Mohammed Aldheeb, Mohammed Abdulmalek (2021) Numerical investigation on the pressure drag of some low-speed airfoils for UAV application. CFD Letters, 13 (2). pp. 29-48. ISSN 2180-1363 http://akademiabaru.com/submit/index.php/cfdl/article/view/3075/2660 https://doi.org/10.37934/cfdl.13.2.2948
institution Universiti Islam Antarabangsa Malaysia
building IIUM Library
collection Institutional Repository
continent Asia
country Malaysia
content_provider International Islamic University Malaysia
content_source IIUM Repository (IREP)
url_provider http://irep.iium.edu.my/
language English
English
topic TL500 Aeronautics
spellingShingle TL500 Aeronautics
Zohary, Aideal Czar
Asrar, Waqar
Mohammed Aldheeb, Mohammed Abdulmalek
Numerical investigation on the pressure drag of some low-speed airfoils for UAV application
description Progressive advancements in small to medium-sized fixed-wing UAVs call for prototype designing to be fast, accurate, and economical. This requires the numerical assessment of airfoil performance to be based on high fidelity replication of wind tunnel data. Furthermore, integration of drag reduction techniques is attractive as improvements in endurance, payload capacity and reduction in carbon footprints can be attained. Since a variety of suitable airfoil geometries are currently available for this application, selecting a fitting candidate can be difficult therefore risking potential gain in efficiency. The aim of this paper is to assist in resolving this issue by investigating the variation in pressure drag and its distribution with respect to the type of airfoil geometry, angle of attack, and the contribution of pressure towards the total drag at low Reynolds numbers. The airfoils selected in this study comprises of the NACA 4415, FX 61-184, E420 and S1223 which are preferred for subsonic UAV applications in addition to having the NACA 0012 serving as a standard profile. Performance of the S1223 airfoil was examined at a chord-based Reynolds number of 0.3 x 106 with the remaining airfoils at 1.0 x 106 for a range of angle of attack of around 0-10°. The unsteady 3-equation Intermittency SST model from ANSYS FLUENT 2020 was utilized with gradual reduction of timestep from 0.001s, 0.0005s, 0.00025s and 0.0001s. Experimental lift and drag validation across the airfoils generally suggest that the transitional model regularly outperforms XFOIL. Among the selection, concave airfoils such as the E420 and S1223 excel in delivering high lift at the expense of an increase in drag. Evaluation of the l/d ratio alone may underestimate their potential. Hence, further studies should focus on the implementation of drag reduction techniques on concave airfoils to enhance their performance. At the maximum tested angle of attack, the E420 reaches a cl value of 2.09 and S1223 at 1.98 while the FX 61-184 only at 1.57 and NACA 4415 at 1.36.
format Article
author Zohary, Aideal Czar
Asrar, Waqar
Mohammed Aldheeb, Mohammed Abdulmalek
author_facet Zohary, Aideal Czar
Asrar, Waqar
Mohammed Aldheeb, Mohammed Abdulmalek
author_sort Zohary, Aideal Czar
title Numerical investigation on the pressure drag of some low-speed airfoils for UAV application
title_short Numerical investigation on the pressure drag of some low-speed airfoils for UAV application
title_full Numerical investigation on the pressure drag of some low-speed airfoils for UAV application
title_fullStr Numerical investigation on the pressure drag of some low-speed airfoils for UAV application
title_full_unstemmed Numerical investigation on the pressure drag of some low-speed airfoils for UAV application
title_sort numerical investigation on the pressure drag of some low-speed airfoils for uav application
publisher ISSR
publishDate 2021
url http://irep.iium.edu.my/89039/7/89309_Numerical%20investigation%20on%20the%20pressure%20drag%20of%20some%20low-speed%20airfoils%20for%20UAV%20application_SCOPUS.pdf
http://irep.iium.edu.my/89039/13/89309_Numerical%20investigation%20on%20the%20pressure%20drag%20of%20some%20low-speed%20airfoils%20for%20UAV%20application.pdf
http://irep.iium.edu.my/89039/
http://akademiabaru.com/submit/index.php/cfdl/article/view/3075/2660
https://doi.org/10.37934/cfdl.13.2.2948
_version_ 1696976085612232704
score 13.211869

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