CFD Simulations and External Shape Optimization of Missile with Wing and Tailfin Configuration to Improve Aerodynamic Performance

The wing of missile can be considered as an effective factor for determination of lift to drag ratio. However, there are few studies that investigate wing effect on missile aerodynamics. Therefore, the purpose of this study is to indicate wing effect on the missile aerodynamics and optimize wing geo...

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Autores principales:	A. Şumnu, İ. H. Güzelbey
Formato:	article
Lenguaje:	EN
Publicado:	Isfahan University of Technology 2021
Materias:	missile aerodynamics; genetic algorithm; multi-objective optimization. Mechanical engineering and machinery TJ1-1570
Acceso en línea:	https://doaj.org/article/54ddfbab4fc44c15ab2639c98b8de7e3
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id	oai:doaj.org-article:54ddfbab4fc44c15ab2639c98b8de7e3
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spelling	oai:doaj.org-article:54ddfbab4fc44c15ab2639c98b8de7e32021-11-13T07:03:04ZCFD Simulations and External Shape Optimization of Missile with Wing and Tailfin Configuration to Improve Aerodynamic Performance1735-3572https://doaj.org/article/54ddfbab4fc44c15ab2639c98b8de7e32021-01-01T00:00:00Zhttp://jafmonline.net/JournalArchive/download?file_ID=57181&issue_ID=1015https://doaj.org/toc/1735-3572The wing of missile can be considered as an effective factor for determination of lift to drag ratio. However, there are few studies that investigate wing effect on missile aerodynamics. Therefore, the purpose of this study is to indicate wing effect on the missile aerodynamics and optimize wing geometry for enhancement of aerodynamic efficiency. The missile designed tail-fin configuration is selected from a previous study which contains experimental data. In the beginning of study, Computational Fluid Dynamics (CFD) simulations of selected missile are performed and compared with experimental data. Wing is then mounted to the selected missile and CFD solution is repeated for modified missile at 6º angle of attach (AoA) and subsonic and supersonic speeds. The modified missile shows good performance in point of aerodynamics when compared with baseline missile model. In addition, wing geometry is optimized to improve aerodynamic performance using Multi-Objective Genetic Algorithm (MOGA). Objective functions are determined as lift and drag coefficients. Wing geometry parameters are determined as design variables for optimization. After the optimization process, the results are showed that the aerodynamic coefficients are improved when compared with baseline geometry. In addition, response surface analysis is presented to show which design parameters are more effective on drag and lift forces. The findings of study show that optimum results are more efficient in terms of performance. CFD solution method and the optimization procedure can be applied to design or optimize for different geometry.A. Şumnuİ. H. GüzelbeyIsfahan University of Technology articlemissile aerodynamics; genetic algorithm; multi-objective optimization.Mechanical engineering and machineryTJ1-1570ENJournal of Applied Fluid Mechanics, Vol 14, Iss 6, Pp 1795-1807 (2021)
institution	DOAJ
collection	DOAJ
language	EN
topic	missile aerodynamics; genetic algorithm; multi-objective optimization. Mechanical engineering and machinery TJ1-1570
spellingShingle	missile aerodynamics; genetic algorithm; multi-objective optimization. Mechanical engineering and machinery TJ1-1570 A. Şumnu İ. H. Güzelbey CFD Simulations and External Shape Optimization of Missile with Wing and Tailfin Configuration to Improve Aerodynamic Performance
description	The wing of missile can be considered as an effective factor for determination of lift to drag ratio. However, there are few studies that investigate wing effect on missile aerodynamics. Therefore, the purpose of this study is to indicate wing effect on the missile aerodynamics and optimize wing geometry for enhancement of aerodynamic efficiency. The missile designed tail-fin configuration is selected from a previous study which contains experimental data. In the beginning of study, Computational Fluid Dynamics (CFD) simulations of selected missile are performed and compared with experimental data. Wing is then mounted to the selected missile and CFD solution is repeated for modified missile at 6º angle of attach (AoA) and subsonic and supersonic speeds. The modified missile shows good performance in point of aerodynamics when compared with baseline missile model. In addition, wing geometry is optimized to improve aerodynamic performance using Multi-Objective Genetic Algorithm (MOGA). Objective functions are determined as lift and drag coefficients. Wing geometry parameters are determined as design variables for optimization. After the optimization process, the results are showed that the aerodynamic coefficients are improved when compared with baseline geometry. In addition, response surface analysis is presented to show which design parameters are more effective on drag and lift forces. The findings of study show that optimum results are more efficient in terms of performance. CFD solution method and the optimization procedure can be applied to design or optimize for different geometry.
format	article
author	A. Şumnu İ. H. Güzelbey
author_facet	A. Şumnu İ. H. Güzelbey
author_sort	A. Şumnu
title	CFD Simulations and External Shape Optimization of Missile with Wing and Tailfin Configuration to Improve Aerodynamic Performance
title_short	CFD Simulations and External Shape Optimization of Missile with Wing and Tailfin Configuration to Improve Aerodynamic Performance
title_full	CFD Simulations and External Shape Optimization of Missile with Wing and Tailfin Configuration to Improve Aerodynamic Performance
title_fullStr	CFD Simulations and External Shape Optimization of Missile with Wing and Tailfin Configuration to Improve Aerodynamic Performance
title_full_unstemmed	CFD Simulations and External Shape Optimization of Missile with Wing and Tailfin Configuration to Improve Aerodynamic Performance
title_sort	cfd simulations and external shape optimization of missile with wing and tailfin configuration to improve aerodynamic performance
publisher	Isfahan University of Technology
publishDate	2021
url	https://doaj.org/article/54ddfbab4fc44c15ab2639c98b8de7e3
work_keys_str_mv	AT asumnu cfdsimulationsandexternalshapeoptimizationofmissilewithwingandtailfinconfigurationtoimproveaerodynamicperformance AT ihguzelbey cfdsimulationsandexternalshapeoptimizationofmissilewithwingandtailfinconfigurationtoimproveaerodynamicperformance
_version_	1718430255651225600

CFD Simulations and External Shape Optimization of Missile with Wing and Tailfin Configuration to Improve Aerodynamic Performance

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