Aerodynamic design of a double slotted morphed flap airfoil– a numerical study

Introduction:The objective of this study is to develop and simulate a double slotted morphed flap with the intention of reducing drag and enhancing lift, thereby leading to a smaller flap size and reduced weight.Methods:A flap was meticulously designed to accommodate conditions at Mach 0.2 and Reyno...
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Autor*in:	S. S. Shahrokhi [verfasserIn] M. Taeibi Rahni [verfasserIn] P. Akbari [verfasserIn]

Format:	E-Artikel
Sprache:	Englisch

Erschienen:	2024

Schlagwörter:	morphing double slotted flap CFD lift drag high-lift device

Übergeordnetes Werk:	In: Frontiers in Mechanical Engineering - Frontiers Media S.A., 2016, 10(2024)
Übergeordnetes Werk:	volume:10 ; year:2024

Links:	Link aufrufen Link aufrufen Link aufrufen Journal toc

DOI / URN:	10.3389/fmech.2024.1371479

Katalog-ID:	DOAJ097186678

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allfieldsSound	10.3389/fmech.2024.1371479 doi (DE-627)DOAJ097186678 (DE-599)DOAJ4adfed44e9934a2fb6b31974a2a3d8ff DE-627 ger DE-627 rakwb eng TJ1-1570 S. S. Shahrokhi verfasserin aut Aerodynamic design of a double slotted morphed flap airfoil– a numerical study 2024 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier Introduction:The objective of this study is to develop and simulate a double slotted morphed flap with the intention of reducing drag and enhancing lift, thereby leading to a smaller flap size and reduced weight.Methods:A flap was meticulously designed to accommodate conditions at Mach 0.2 and Reynolds numbers of 4.7×106. To conduct the simulation, ANSYS FLUENT flow solver and POINTWISE grid generator were utilized. The morphing technique employed involved adjusting both flap mean camber and flap slots, ensuring minimal flow interferences. By discretizing the flap mean camber line, various flap geometries were achieved.Results and Discussions:The findings reveal a significant enhancement in the airfoil’s aerodynamic efficiency attributed to the implementation of the new flap design. The study shows that utilizing double-slotted morphing in the NACA 4412 airfoil at a 30° flap deflection angle increased the lift coefficient by 82% compared to the un-morphed state. A comparison of lift coefficients between this research and the NACA 4412 split flap at a 60° deflection angle indicates that the double-slotted morphing in the NACA 4412 airfoil at a smaller deflection angle of 30° results in a 14% higher maximum lift coefficient. morphing double slotted flap CFD lift drag high-lift device Mechanical engineering and machinery M. Taeibi Rahni verfasserin aut P. Akbari verfasserin aut In Frontiers in Mechanical Engineering Frontiers Media S.A., 2016 10(2024) (DE-627)835892271 (DE-600)2835636-6 22973079 nnns volume:10 year:2024 https://doi.org/10.3389/fmech.2024.1371479 kostenfrei https://doaj.org/article/4adfed44e9934a2fb6b31974a2a3d8ff kostenfrei https://www.frontiersin.org/articles/10.3389/fmech.2024.1371479/full kostenfrei https://doaj.org/toc/2297-3079 Journal toc kostenfrei GBV_USEFLAG_A SYSFLAG_A GBV_DOAJ GBV_ILN_11 GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_39 GBV_ILN_40 GBV_ILN_60 GBV_ILN_62 GBV_ILN_63 GBV_ILN_65 GBV_ILN_69 GBV_ILN_70 GBV_ILN_73 GBV_ILN_95 GBV_ILN_105 GBV_ILN_110 GBV_ILN_151 GBV_ILN_161 GBV_ILN_170 GBV_ILN_213 GBV_ILN_230 GBV_ILN_285 GBV_ILN_293 GBV_ILN_370 GBV_ILN_602 GBV_ILN_2003 GBV_ILN_2014 GBV_ILN_4012 GBV_ILN_4037 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4126 GBV_ILN_4249 GBV_ILN_4305 GBV_ILN_4306 GBV_ILN_4307 GBV_ILN_4313 GBV_ILN_4322 GBV_ILN_4323 GBV_ILN_4324 GBV_ILN_4325 GBV_ILN_4335 GBV_ILN_4338 GBV_ILN_4367 GBV_ILN_4700 AR 10 2024
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Shahrokhi</subfield><subfield code="e">verfasserin</subfield><subfield code="4">aut</subfield></datafield><datafield tag="245" ind1="1" ind2="0"><subfield code="a">Aerodynamic design of a double slotted morphed flap airfoil– a numerical study</subfield></datafield><datafield tag="264" ind1=" " ind2="1"><subfield code="c">2024</subfield></datafield><datafield tag="336" ind1=" " ind2=" "><subfield code="a">Text</subfield><subfield code="b">txt</subfield><subfield code="2">rdacontent</subfield></datafield><datafield tag="337" ind1=" " ind2=" "><subfield code="a">Computermedien</subfield><subfield code="b">c</subfield><subfield code="2">rdamedia</subfield></datafield><datafield tag="338" ind1=" " ind2=" "><subfield code="a">Online-Ressource</subfield><subfield code="b">cr</subfield><subfield code="2">rdacarrier</subfield></datafield><datafield tag="520" ind1=" " ind2=" "><subfield code="a">Introduction:The objective of this study is to develop and simulate a double slotted morphed flap with the intention of reducing drag and enhancing lift, thereby leading to a smaller flap size and reduced weight.Methods:A flap was meticulously designed to accommodate conditions at Mach 0.2 and Reynolds numbers of 4.7×106. To conduct the simulation, ANSYS FLUENT flow solver and POINTWISE grid generator were utilized. The morphing technique employed involved adjusting both flap mean camber and flap slots, ensuring minimal flow interferences. By discretizing the flap mean camber line, various flap geometries were achieved.Results and Discussions:The findings reveal a significant enhancement in the airfoil’s aerodynamic efficiency attributed to the implementation of the new flap design. The study shows that utilizing double-slotted morphing in the NACA 4412 airfoil at a 30° flap deflection angle increased the lift coefficient by 82% compared to the un-morphed state. 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callnumber-first	T - Technology
author	S. S. Shahrokhi
spellingShingle	S. S. Shahrokhi misc TJ1-1570 misc morphing misc double slotted flap misc CFD misc lift misc drag misc high-lift device misc Mechanical engineering and machinery Aerodynamic design of a double slotted morphed flap airfoil– a numerical study
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topic_title	TJ1-1570 Aerodynamic design of a double slotted morphed flap airfoil– a numerical study morphing double slotted flap CFD lift drag high-lift device
topic	misc TJ1-1570 misc morphing misc double slotted flap misc CFD misc lift misc drag misc high-lift device misc Mechanical engineering and machinery
topic_unstemmed	misc TJ1-1570 misc morphing misc double slotted flap misc CFD misc lift misc drag misc high-lift device misc Mechanical engineering and machinery
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title	Aerodynamic design of a double slotted morphed flap airfoil– a numerical study
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title_full	Aerodynamic design of a double slotted morphed flap airfoil– a numerical study
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title_sort	aerodynamic design of a double slotted morphed flap airfoil– a numerical study
callnumber	TJ1-1570
title_auth	Aerodynamic design of a double slotted morphed flap airfoil– a numerical study
abstract	Introduction:The objective of this study is to develop and simulate a double slotted morphed flap with the intention of reducing drag and enhancing lift, thereby leading to a smaller flap size and reduced weight.Methods:A flap was meticulously designed to accommodate conditions at Mach 0.2 and Reynolds numbers of 4.7×106. To conduct the simulation, ANSYS FLUENT flow solver and POINTWISE grid generator were utilized. The morphing technique employed involved adjusting both flap mean camber and flap slots, ensuring minimal flow interferences. By discretizing the flap mean camber line, various flap geometries were achieved.Results and Discussions:The findings reveal a significant enhancement in the airfoil’s aerodynamic efficiency attributed to the implementation of the new flap design. The study shows that utilizing double-slotted morphing in the NACA 4412 airfoil at a 30° flap deflection angle increased the lift coefficient by 82% compared to the un-morphed state. A comparison of lift coefficients between this research and the NACA 4412 split flap at a 60° deflection angle indicates that the double-slotted morphing in the NACA 4412 airfoil at a smaller deflection angle of 30° results in a 14% higher maximum lift coefficient.
abstractGer	Introduction:The objective of this study is to develop and simulate a double slotted morphed flap with the intention of reducing drag and enhancing lift, thereby leading to a smaller flap size and reduced weight.Methods:A flap was meticulously designed to accommodate conditions at Mach 0.2 and Reynolds numbers of 4.7×106. To conduct the simulation, ANSYS FLUENT flow solver and POINTWISE grid generator were utilized. The morphing technique employed involved adjusting both flap mean camber and flap slots, ensuring minimal flow interferences. By discretizing the flap mean camber line, various flap geometries were achieved.Results and Discussions:The findings reveal a significant enhancement in the airfoil’s aerodynamic efficiency attributed to the implementation of the new flap design. The study shows that utilizing double-slotted morphing in the NACA 4412 airfoil at a 30° flap deflection angle increased the lift coefficient by 82% compared to the un-morphed state. A comparison of lift coefficients between this research and the NACA 4412 split flap at a 60° deflection angle indicates that the double-slotted morphing in the NACA 4412 airfoil at a smaller deflection angle of 30° results in a 14% higher maximum lift coefficient.
abstract_unstemmed	Introduction:The objective of this study is to develop and simulate a double slotted morphed flap with the intention of reducing drag and enhancing lift, thereby leading to a smaller flap size and reduced weight.Methods:A flap was meticulously designed to accommodate conditions at Mach 0.2 and Reynolds numbers of 4.7×106. To conduct the simulation, ANSYS FLUENT flow solver and POINTWISE grid generator were utilized. The morphing technique employed involved adjusting both flap mean camber and flap slots, ensuring minimal flow interferences. By discretizing the flap mean camber line, various flap geometries were achieved.Results and Discussions:The findings reveal a significant enhancement in the airfoil’s aerodynamic efficiency attributed to the implementation of the new flap design. The study shows that utilizing double-slotted morphing in the NACA 4412 airfoil at a 30° flap deflection angle increased the lift coefficient by 82% compared to the un-morphed state. A comparison of lift coefficients between this research and the NACA 4412 split flap at a 60° deflection angle indicates that the double-slotted morphing in the NACA 4412 airfoil at a smaller deflection angle of 30° results in a 14% higher maximum lift coefficient.
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title_short	Aerodynamic design of a double slotted morphed flap airfoil– a numerical study
url	https://doi.org/10.3389/fmech.2024.1371479 https://doaj.org/article/4adfed44e9934a2fb6b31974a2a3d8ff https://www.frontiersin.org/articles/10.3389/fmech.2024.1371479/full https://doaj.org/toc/2297-3079
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Aerodynamic design of a double slotted morphed flap airfoil– a numerical study

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