Numerical Study on Combustion-Driven Jet Actuation for Aerodynamic Control of Airfoil Flows

In this study, a numerical investigation is conducted on combustion-driven pulsed-jet actuation to control the flow around a lifting surface. Based on relevant experimental measurements and computations, high-speed jets are generated from the impulsive variation in pressure at the actuator boundary....
Ausführliche Beschreibung

Gespeichert in:

Autor*in:	Taesoon Kim [verfasserIn] Suhyeon Park [verfasserIn] Ilyoup Sohn [verfasserIn]

Format:	E-Artikel
Sprache:	Englisch

Erschienen:	2023

Schlagwörter:	combustion-powered actuation active flow control impulse jet actuation flow separation computational fluid dynamics

Übergeordnetes Werk:	In: Energies - MDPI AG, 2008, 16(2023), 24, p 8008
Übergeordnetes Werk:	volume:16 ; year:2023 ; number:24, p 8008

Links:	Link aufrufen Link aufrufen Link aufrufen Journal toc

DOI / URN:	10.3390/en16248008

Katalog-ID:	DOAJ098878859

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520			\|a In this study, a numerical investigation is conducted on combustion-driven pulsed-jet actuation to control the flow around a lifting surface. Based on relevant experimental measurements and computations, high-speed jets are generated from the impulsive variation in pressure at the actuator boundary. A supersonic jet flow is momentarily generated by combustion in a reaction chamber of the actuator, and the flow interacts with the external flow around the lifting surface and alters the aerodynamic characteristics. The computational results indicate that the flow control performance of the jet actuation is significant at a high-incidence angle of attack, such as beyond the stall angle, whereas the impact is minimal at low angles of attack, such as in the linear lift region. Repetitive jet actuation can produce additional momentum to the external flow and alters the pressure distribution on the suction surface, particularly downstream of the actuator location. This pressure variation from the actuation yields an additional lift force on the lifting surface and reduces the amplitude of the aerodynamic moment at a given angle of attack, thus enhancing the aerodynamic performance of the airfoil.
650		4	\|a combustion-powered actuation
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allfields	10.3390/en16248008 doi (DE-627)DOAJ098878859 (DE-599)DOAJ5f55321cc95f4489bbffafc5c0c9cc3d DE-627 ger DE-627 rakwb eng Taesoon Kim verfasserin aut Numerical Study on Combustion-Driven Jet Actuation for Aerodynamic Control of Airfoil Flows 2023 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier In this study, a numerical investigation is conducted on combustion-driven pulsed-jet actuation to control the flow around a lifting surface. Based on relevant experimental measurements and computations, high-speed jets are generated from the impulsive variation in pressure at the actuator boundary. A supersonic jet flow is momentarily generated by combustion in a reaction chamber of the actuator, and the flow interacts with the external flow around the lifting surface and alters the aerodynamic characteristics. The computational results indicate that the flow control performance of the jet actuation is significant at a high-incidence angle of attack, such as beyond the stall angle, whereas the impact is minimal at low angles of attack, such as in the linear lift region. Repetitive jet actuation can produce additional momentum to the external flow and alters the pressure distribution on the suction surface, particularly downstream of the actuator location. This pressure variation from the actuation yields an additional lift force on the lifting surface and reduces the amplitude of the aerodynamic moment at a given angle of attack, thus enhancing the aerodynamic performance of the airfoil. combustion-powered actuation active flow control impulse jet actuation flow separation computational fluid dynamics Technology T Suhyeon Park verfasserin aut Ilyoup Sohn verfasserin aut In Energies MDPI AG, 2008 16(2023), 24, p 8008 (DE-627)572083742 (DE-600)2437446-5 19961073 nnns volume:16 year:2023 number:24, p 8008 https://doi.org/10.3390/en16248008 kostenfrei https://doaj.org/article/5f55321cc95f4489bbffafc5c0c9cc3d kostenfrei https://www.mdpi.com/1996-1073/16/24/8008 kostenfrei https://doaj.org/toc/1996-1073 Journal toc kostenfrei GBV_USEFLAG_A SYSFLAG_A GBV_DOAJ 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_206 GBV_ILN_213 GBV_ILN_230 GBV_ILN_285 GBV_ILN_293 GBV_ILN_370 GBV_ILN_602 GBV_ILN_2005 GBV_ILN_2009 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2055 GBV_ILN_2108 GBV_ILN_2111 GBV_ILN_2119 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 16 2023 24, p 8008
spelling	10.3390/en16248008 doi (DE-627)DOAJ098878859 (DE-599)DOAJ5f55321cc95f4489bbffafc5c0c9cc3d DE-627 ger DE-627 rakwb eng Taesoon Kim verfasserin aut Numerical Study on Combustion-Driven Jet Actuation for Aerodynamic Control of Airfoil Flows 2023 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier In this study, a numerical investigation is conducted on combustion-driven pulsed-jet actuation to control the flow around a lifting surface. Based on relevant experimental measurements and computations, high-speed jets are generated from the impulsive variation in pressure at the actuator boundary. A supersonic jet flow is momentarily generated by combustion in a reaction chamber of the actuator, and the flow interacts with the external flow around the lifting surface and alters the aerodynamic characteristics. The computational results indicate that the flow control performance of the jet actuation is significant at a high-incidence angle of attack, such as beyond the stall angle, whereas the impact is minimal at low angles of attack, such as in the linear lift region. Repetitive jet actuation can produce additional momentum to the external flow and alters the pressure distribution on the suction surface, particularly downstream of the actuator location. This pressure variation from the actuation yields an additional lift force on the lifting surface and reduces the amplitude of the aerodynamic moment at a given angle of attack, thus enhancing the aerodynamic performance of the airfoil. combustion-powered actuation active flow control impulse jet actuation flow separation computational fluid dynamics Technology T Suhyeon Park verfasserin aut Ilyoup Sohn verfasserin aut In Energies MDPI AG, 2008 16(2023), 24, p 8008 (DE-627)572083742 (DE-600)2437446-5 19961073 nnns volume:16 year:2023 number:24, p 8008 https://doi.org/10.3390/en16248008 kostenfrei https://doaj.org/article/5f55321cc95f4489bbffafc5c0c9cc3d kostenfrei https://www.mdpi.com/1996-1073/16/24/8008 kostenfrei https://doaj.org/toc/1996-1073 Journal toc kostenfrei GBV_USEFLAG_A SYSFLAG_A GBV_DOAJ 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_206 GBV_ILN_213 GBV_ILN_230 GBV_ILN_285 GBV_ILN_293 GBV_ILN_370 GBV_ILN_602 GBV_ILN_2005 GBV_ILN_2009 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2055 GBV_ILN_2108 GBV_ILN_2111 GBV_ILN_2119 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 16 2023 24, p 8008
allfields_unstemmed	10.3390/en16248008 doi (DE-627)DOAJ098878859 (DE-599)DOAJ5f55321cc95f4489bbffafc5c0c9cc3d DE-627 ger DE-627 rakwb eng Taesoon Kim verfasserin aut Numerical Study on Combustion-Driven Jet Actuation for Aerodynamic Control of Airfoil Flows 2023 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier In this study, a numerical investigation is conducted on combustion-driven pulsed-jet actuation to control the flow around a lifting surface. Based on relevant experimental measurements and computations, high-speed jets are generated from the impulsive variation in pressure at the actuator boundary. A supersonic jet flow is momentarily generated by combustion in a reaction chamber of the actuator, and the flow interacts with the external flow around the lifting surface and alters the aerodynamic characteristics. The computational results indicate that the flow control performance of the jet actuation is significant at a high-incidence angle of attack, such as beyond the stall angle, whereas the impact is minimal at low angles of attack, such as in the linear lift region. Repetitive jet actuation can produce additional momentum to the external flow and alters the pressure distribution on the suction surface, particularly downstream of the actuator location. This pressure variation from the actuation yields an additional lift force on the lifting surface and reduces the amplitude of the aerodynamic moment at a given angle of attack, thus enhancing the aerodynamic performance of the airfoil. combustion-powered actuation active flow control impulse jet actuation flow separation computational fluid dynamics Technology T Suhyeon Park verfasserin aut Ilyoup Sohn verfasserin aut In Energies MDPI AG, 2008 16(2023), 24, p 8008 (DE-627)572083742 (DE-600)2437446-5 19961073 nnns volume:16 year:2023 number:24, p 8008 https://doi.org/10.3390/en16248008 kostenfrei https://doaj.org/article/5f55321cc95f4489bbffafc5c0c9cc3d kostenfrei https://www.mdpi.com/1996-1073/16/24/8008 kostenfrei https://doaj.org/toc/1996-1073 Journal toc kostenfrei GBV_USEFLAG_A SYSFLAG_A GBV_DOAJ 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_206 GBV_ILN_213 GBV_ILN_230 GBV_ILN_285 GBV_ILN_293 GBV_ILN_370 GBV_ILN_602 GBV_ILN_2005 GBV_ILN_2009 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2055 GBV_ILN_2108 GBV_ILN_2111 GBV_ILN_2119 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 16 2023 24, p 8008
allfieldsGer	10.3390/en16248008 doi (DE-627)DOAJ098878859 (DE-599)DOAJ5f55321cc95f4489bbffafc5c0c9cc3d DE-627 ger DE-627 rakwb eng Taesoon Kim verfasserin aut Numerical Study on Combustion-Driven Jet Actuation for Aerodynamic Control of Airfoil Flows 2023 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier In this study, a numerical investigation is conducted on combustion-driven pulsed-jet actuation to control the flow around a lifting surface. Based on relevant experimental measurements and computations, high-speed jets are generated from the impulsive variation in pressure at the actuator boundary. A supersonic jet flow is momentarily generated by combustion in a reaction chamber of the actuator, and the flow interacts with the external flow around the lifting surface and alters the aerodynamic characteristics. The computational results indicate that the flow control performance of the jet actuation is significant at a high-incidence angle of attack, such as beyond the stall angle, whereas the impact is minimal at low angles of attack, such as in the linear lift region. Repetitive jet actuation can produce additional momentum to the external flow and alters the pressure distribution on the suction surface, particularly downstream of the actuator location. This pressure variation from the actuation yields an additional lift force on the lifting surface and reduces the amplitude of the aerodynamic moment at a given angle of attack, thus enhancing the aerodynamic performance of the airfoil. combustion-powered actuation active flow control impulse jet actuation flow separation computational fluid dynamics Technology T Suhyeon Park verfasserin aut Ilyoup Sohn verfasserin aut In Energies MDPI AG, 2008 16(2023), 24, p 8008 (DE-627)572083742 (DE-600)2437446-5 19961073 nnns volume:16 year:2023 number:24, p 8008 https://doi.org/10.3390/en16248008 kostenfrei https://doaj.org/article/5f55321cc95f4489bbffafc5c0c9cc3d kostenfrei https://www.mdpi.com/1996-1073/16/24/8008 kostenfrei https://doaj.org/toc/1996-1073 Journal toc kostenfrei GBV_USEFLAG_A SYSFLAG_A GBV_DOAJ 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_206 GBV_ILN_213 GBV_ILN_230 GBV_ILN_285 GBV_ILN_293 GBV_ILN_370 GBV_ILN_602 GBV_ILN_2005 GBV_ILN_2009 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2055 GBV_ILN_2108 GBV_ILN_2111 GBV_ILN_2119 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 16 2023 24, p 8008
allfieldsSound	10.3390/en16248008 doi (DE-627)DOAJ098878859 (DE-599)DOAJ5f55321cc95f4489bbffafc5c0c9cc3d DE-627 ger DE-627 rakwb eng Taesoon Kim verfasserin aut Numerical Study on Combustion-Driven Jet Actuation for Aerodynamic Control of Airfoil Flows 2023 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier In this study, a numerical investigation is conducted on combustion-driven pulsed-jet actuation to control the flow around a lifting surface. Based on relevant experimental measurements and computations, high-speed jets are generated from the impulsive variation in pressure at the actuator boundary. A supersonic jet flow is momentarily generated by combustion in a reaction chamber of the actuator, and the flow interacts with the external flow around the lifting surface and alters the aerodynamic characteristics. The computational results indicate that the flow control performance of the jet actuation is significant at a high-incidence angle of attack, such as beyond the stall angle, whereas the impact is minimal at low angles of attack, such as in the linear lift region. Repetitive jet actuation can produce additional momentum to the external flow and alters the pressure distribution on the suction surface, particularly downstream of the actuator location. This pressure variation from the actuation yields an additional lift force on the lifting surface and reduces the amplitude of the aerodynamic moment at a given angle of attack, thus enhancing the aerodynamic performance of the airfoil. combustion-powered actuation active flow control impulse jet actuation flow separation computational fluid dynamics Technology T Suhyeon Park verfasserin aut Ilyoup Sohn verfasserin aut In Energies MDPI AG, 2008 16(2023), 24, p 8008 (DE-627)572083742 (DE-600)2437446-5 19961073 nnns volume:16 year:2023 number:24, p 8008 https://doi.org/10.3390/en16248008 kostenfrei https://doaj.org/article/5f55321cc95f4489bbffafc5c0c9cc3d kostenfrei https://www.mdpi.com/1996-1073/16/24/8008 kostenfrei https://doaj.org/toc/1996-1073 Journal toc kostenfrei GBV_USEFLAG_A SYSFLAG_A GBV_DOAJ 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_206 GBV_ILN_213 GBV_ILN_230 GBV_ILN_285 GBV_ILN_293 GBV_ILN_370 GBV_ILN_602 GBV_ILN_2005 GBV_ILN_2009 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2055 GBV_ILN_2108 GBV_ILN_2111 GBV_ILN_2119 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 16 2023 24, p 8008
language	English
source	In Energies 16(2023), 24, p 8008 volume:16 year:2023 number:24, p 8008
sourceStr	In Energies 16(2023), 24, p 8008 volume:16 year:2023 number:24, p 8008
format_phy_str_mv	Article
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topic_facet	combustion-powered actuation active flow control impulse jet actuation flow separation computational fluid dynamics Technology T
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container_title	Energies
authorswithroles_txt_mv	Taesoon Kim @@aut@@ Suhyeon Park @@aut@@ Ilyoup Sohn @@aut@@
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author	Taesoon Kim
spellingShingle	Taesoon Kim misc combustion-powered actuation misc active flow control misc impulse jet actuation misc flow separation misc computational fluid dynamics misc Technology misc T Numerical Study on Combustion-Driven Jet Actuation for Aerodynamic Control of Airfoil Flows
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topic_title	Numerical Study on Combustion-Driven Jet Actuation for Aerodynamic Control of Airfoil Flows combustion-powered actuation active flow control impulse jet actuation flow separation computational fluid dynamics
topic	misc combustion-powered actuation misc active flow control misc impulse jet actuation misc flow separation misc computational fluid dynamics misc Technology misc T
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title	Numerical Study on Combustion-Driven Jet Actuation for Aerodynamic Control of Airfoil Flows
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title_sort	numerical study on combustion-driven jet actuation for aerodynamic control of airfoil flows
title_auth	Numerical Study on Combustion-Driven Jet Actuation for Aerodynamic Control of Airfoil Flows
abstract	In this study, a numerical investigation is conducted on combustion-driven pulsed-jet actuation to control the flow around a lifting surface. Based on relevant experimental measurements and computations, high-speed jets are generated from the impulsive variation in pressure at the actuator boundary. A supersonic jet flow is momentarily generated by combustion in a reaction chamber of the actuator, and the flow interacts with the external flow around the lifting surface and alters the aerodynamic characteristics. The computational results indicate that the flow control performance of the jet actuation is significant at a high-incidence angle of attack, such as beyond the stall angle, whereas the impact is minimal at low angles of attack, such as in the linear lift region. Repetitive jet actuation can produce additional momentum to the external flow and alters the pressure distribution on the suction surface, particularly downstream of the actuator location. This pressure variation from the actuation yields an additional lift force on the lifting surface and reduces the amplitude of the aerodynamic moment at a given angle of attack, thus enhancing the aerodynamic performance of the airfoil.
abstractGer	In this study, a numerical investigation is conducted on combustion-driven pulsed-jet actuation to control the flow around a lifting surface. Based on relevant experimental measurements and computations, high-speed jets are generated from the impulsive variation in pressure at the actuator boundary. A supersonic jet flow is momentarily generated by combustion in a reaction chamber of the actuator, and the flow interacts with the external flow around the lifting surface and alters the aerodynamic characteristics. The computational results indicate that the flow control performance of the jet actuation is significant at a high-incidence angle of attack, such as beyond the stall angle, whereas the impact is minimal at low angles of attack, such as in the linear lift region. Repetitive jet actuation can produce additional momentum to the external flow and alters the pressure distribution on the suction surface, particularly downstream of the actuator location. This pressure variation from the actuation yields an additional lift force on the lifting surface and reduces the amplitude of the aerodynamic moment at a given angle of attack, thus enhancing the aerodynamic performance of the airfoil.
abstract_unstemmed	In this study, a numerical investigation is conducted on combustion-driven pulsed-jet actuation to control the flow around a lifting surface. Based on relevant experimental measurements and computations, high-speed jets are generated from the impulsive variation in pressure at the actuator boundary. A supersonic jet flow is momentarily generated by combustion in a reaction chamber of the actuator, and the flow interacts with the external flow around the lifting surface and alters the aerodynamic characteristics. The computational results indicate that the flow control performance of the jet actuation is significant at a high-incidence angle of attack, such as beyond the stall angle, whereas the impact is minimal at low angles of attack, such as in the linear lift region. Repetitive jet actuation can produce additional momentum to the external flow and alters the pressure distribution on the suction surface, particularly downstream of the actuator location. This pressure variation from the actuation yields an additional lift force on the lifting surface and reduces the amplitude of the aerodynamic moment at a given angle of attack, thus enhancing the aerodynamic performance of the airfoil.
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title_short	Numerical Study on Combustion-Driven Jet Actuation for Aerodynamic Control of Airfoil Flows
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Numerical Study on Combustion-Driven Jet Actuation for Aerodynamic Control of Airfoil Flows

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