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UAV NACA4415 wing structural performance analysis subjected to external aerodynamic load using Schrenk’s approximation

Structural analysis is widely used in the analysis of aircraft structures with the common application of the finite element method. The optimum structural design of aircraft wing is the crucial aspect in the performance of the aircraft considering the high stiffness-to-weight...

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Main Authors: Basri, Ernnie Illyani, Basri, Adi Azriff, Abas, Mohd. Firdaus, Mustapha, Faizal, Hameed Sultan, Mohamed Thariq, Ahmad, Kamarul Arifin
Format: Article
Language:English
Published: Penerbit Akademia Baru 2019
Online Access:http://psasir.upm.edu.my/id/eprint/82455/1/UAV%20NACA4415%20wing%20.pdf
http://psasir.upm.edu.my/id/eprint/82455/
https://akademiabaru.com/submit/index.php/arfmts/article/view/2642
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spelling my.upm.eprints.824552021-09-29T13:13:03Z http://psasir.upm.edu.my/id/eprint/82455/ UAV NACA4415 wing structural performance analysis subjected to external aerodynamic load using Schrenk’s approximation Basri, Ernnie Illyani Basri, Adi Azriff Abas, Mohd. Firdaus Mustapha, Faizal Hameed Sultan, Mohamed Thariq Ahmad, Kamarul Arifin Structural analysis is widely used in the analysis of aircraft structures with the common application of the finite element method. The optimum structural design of aircraft wing is the crucial aspect in the performance of the aircraft considering the high stiffness-to-weight ratio and sustain maneuvering condition. In this study, the structural analysis is carried out on the two types of NACA4415 leading edge wing, namely conventional and tubercles. The analysis involves the combination of internal structures that contributed towards the optimization of increase the strength of the wing.Tubercles at the leading edge (TLE) wing commonly known for its superior aerodynamic performancein Computational Fluid Dynamic (CFD) analysis. Whereas, Schrenk’s approximation method is usedto estimate aerodynamic load acting on aircraft lifting surfaces by predicting lift distribution along wing span. The structural static analysis is performed with the aid of computational finite element software, ANSYS 16.1 in order to determine stress and displacement distribution on the selected wing. Slight difference of both stress and displacement 0.4% and 0.1% as compared to conventional ones, thus proven that the design of TLE is acceptable for both aerodynamic and structural conditions. Hence, the result which showed that the composition of internal structures influences the strength of the wing in respect to the different pattern of leading edge. Penerbit Akademia Baru 2019 Article PeerReviewed text en http://psasir.upm.edu.my/id/eprint/82455/1/UAV%20NACA4415%20wing%20.pdf Basri, Ernnie Illyani and Basri, Adi Azriff and Abas, Mohd. Firdaus and Mustapha, Faizal and Hameed Sultan, Mohamed Thariq and Ahmad, Kamarul Arifin (2019) UAV NACA4415 wing structural performance analysis subjected to external aerodynamic load using Schrenk’s approximation. Journal of Advanced Research in Fluid Mechanics and Thermal Sciences, 60 (2). pp. 178-190. ISSN 2289-7879 https://akademiabaru.com/submit/index.php/arfmts/article/view/2642
institution Universiti Putra Malaysia
building UPM Library
collection Institutional Repository
continent Asia
country Malaysia
content_provider Universiti Putra Malaysia
content_source UPM Institutional Repository
url_provider http://psasir.upm.edu.my/
language English
description Structural analysis is widely used in the analysis of aircraft structures with the common application of the finite element method. The optimum structural design of aircraft wing is the crucial aspect in the performance of the aircraft considering the high stiffness-to-weight ratio and sustain maneuvering condition. In this study, the structural analysis is carried out on the two types of NACA4415 leading edge wing, namely conventional and tubercles. The analysis involves the combination of internal structures that contributed towards the optimization of increase the strength of the wing.Tubercles at the leading edge (TLE) wing commonly known for its superior aerodynamic performancein Computational Fluid Dynamic (CFD) analysis. Whereas, Schrenk’s approximation method is usedto estimate aerodynamic load acting on aircraft lifting surfaces by predicting lift distribution along wing span. The structural static analysis is performed with the aid of computational finite element software, ANSYS 16.1 in order to determine stress and displacement distribution on the selected wing. Slight difference of both stress and displacement 0.4% and 0.1% as compared to conventional ones, thus proven that the design of TLE is acceptable for both aerodynamic and structural conditions. Hence, the result which showed that the composition of internal structures influences the strength of the wing in respect to the different pattern of leading edge.
format Article
author Basri, Ernnie Illyani
Basri, Adi Azriff
Abas, Mohd. Firdaus
Mustapha, Faizal
Hameed Sultan, Mohamed Thariq
Ahmad, Kamarul Arifin
spellingShingle Basri, Ernnie Illyani
Basri, Adi Azriff
Abas, Mohd. Firdaus
Mustapha, Faizal
Hameed Sultan, Mohamed Thariq
Ahmad, Kamarul Arifin
UAV NACA4415 wing structural performance analysis subjected to external aerodynamic load using Schrenk’s approximation
author_facet Basri, Ernnie Illyani
Basri, Adi Azriff
Abas, Mohd. Firdaus
Mustapha, Faizal
Hameed Sultan, Mohamed Thariq
Ahmad, Kamarul Arifin
author_sort Basri, Ernnie Illyani
title UAV NACA4415 wing structural performance analysis subjected to external aerodynamic load using Schrenk’s approximation
title_short UAV NACA4415 wing structural performance analysis subjected to external aerodynamic load using Schrenk’s approximation
title_full UAV NACA4415 wing structural performance analysis subjected to external aerodynamic load using Schrenk’s approximation
title_fullStr UAV NACA4415 wing structural performance analysis subjected to external aerodynamic load using Schrenk’s approximation
title_full_unstemmed UAV NACA4415 wing structural performance analysis subjected to external aerodynamic load using Schrenk’s approximation
title_sort uav naca4415 wing structural performance analysis subjected to external aerodynamic load using schrenk’s approximation
publisher Penerbit Akademia Baru
publishDate 2019
url http://psasir.upm.edu.my/id/eprint/82455/1/UAV%20NACA4415%20wing%20.pdf
http://psasir.upm.edu.my/id/eprint/82455/
https://akademiabaru.com/submit/index.php/arfmts/article/view/2642
_version_ 1713201293444513792
score 13.211869

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