Numerical Design of Leading Edge Flow Control over Swept High-Lift Airfoil
Abstract The present paper presents the numerical design of a leading edge flow control methodology over a swept two-element high-lift airfoil using steady state blowing through vortex generator jets. In baseline cases without flow control a turbulent leading-edge type of stall has been observed, th...
Ausführliche Beschreibung
Gespeichert in:
| Autor*in: |
Mahmood, S. [verfasserIn] |
|---|
| Format: |
E-Artikel |
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| Sprache: |
Englisch |
| Erschienen: |
2013 |
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| Anmerkung: |
© AIDAA Associazione Italiana di Aeronautica e Astronautica 2013 |
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| Übergeordnetes Werk: |
Enthalten in: Aerotecnica missili & spazio - [Cham] : Springer International Publishing, 2001, 92(2013), 1-2 vom: 01. Jan., Seite 3-16 |
|---|---|
| Übergeordnetes Werk: |
volume:92 ; year:2013 ; number:1-2 ; day:01 ; month:01 ; pages:3-16 |
| Links: |
|---|
| DOI / URN: |
10.1007/BF03404659 |
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| Katalog-ID: |
SPR038612453 |
|---|
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| 520 | |a Abstract The present paper presents the numerical design of a leading edge flow control methodology over a swept two-element high-lift airfoil using steady state blowing through vortex generator jets. In baseline cases without flow control a turbulent leading-edge type of stall has been observed, therefore the vortex generator jets are applied at the leading edge of the airfoil to prevent separations and thus increase maximum lift and maximum angle of attack, respectively. The design of the flow control setup involves the variation of several geometrical and operational key parameters of the vortex generator jets, such as the pitch angle, skew angle, blowing ratio, sense of rotation and spanwise spacing of two adjacent jets. The results show that the numerical design of leading edge flow control is feasible for such wing arrangement. They show a significant degree of stall suppression over the swept high-lift airfoil. | ||
| 700 | 1 | |a Scholz, P. |4 aut | |
| 700 | 1 | |a Radespiel, R. |4 aut | |
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10.1007/BF03404659 doi (DE-627)SPR038612453 (SPR)BF03404659-e DE-627 ger DE-627 rakwb eng Mahmood, S. verfasserin aut Numerical Design of Leading Edge Flow Control over Swept High-Lift Airfoil 2013 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier © AIDAA Associazione Italiana di Aeronautica e Astronautica 2013 Abstract The present paper presents the numerical design of a leading edge flow control methodology over a swept two-element high-lift airfoil using steady state blowing through vortex generator jets. In baseline cases without flow control a turbulent leading-edge type of stall has been observed, therefore the vortex generator jets are applied at the leading edge of the airfoil to prevent separations and thus increase maximum lift and maximum angle of attack, respectively. The design of the flow control setup involves the variation of several geometrical and operational key parameters of the vortex generator jets, such as the pitch angle, skew angle, blowing ratio, sense of rotation and spanwise spacing of two adjacent jets. The results show that the numerical design of leading edge flow control is feasible for such wing arrangement. They show a significant degree of stall suppression over the swept high-lift airfoil. Scholz, P. aut Radespiel, R. aut Enthalten in Aerotecnica missili & spazio [Cham] : Springer International Publishing, 2001 92(2013), 1-2 vom: 01. Jan., Seite 3-16 (DE-627)1047764040 (DE-600)2960384-5 2524-6968 nnns volume:92 year:2013 number:1-2 day:01 month:01 pages:3-16 https://dx.doi.org/10.1007/BF03404659 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_SPRINGER GBV_ILN_11 GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_32 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_74 GBV_ILN_90 GBV_ILN_95 GBV_ILN_100 GBV_ILN_105 GBV_ILN_110 GBV_ILN_138 GBV_ILN_150 GBV_ILN_151 GBV_ILN_161 GBV_ILN_170 GBV_ILN_171 GBV_ILN_187 GBV_ILN_213 GBV_ILN_224 GBV_ILN_230 GBV_ILN_250 GBV_ILN_281 GBV_ILN_285 GBV_ILN_293 GBV_ILN_370 GBV_ILN_602 GBV_ILN_636 GBV_ILN_702 GBV_ILN_2001 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2006 GBV_ILN_2007 GBV_ILN_2008 GBV_ILN_2009 GBV_ILN_2010 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2026 GBV_ILN_2027 GBV_ILN_2031 GBV_ILN_2034 GBV_ILN_2037 GBV_ILN_2038 GBV_ILN_2039 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2055 GBV_ILN_2057 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2088 GBV_ILN_2093 GBV_ILN_2106 GBV_ILN_2107 GBV_ILN_2108 GBV_ILN_2110 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2118 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2144 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2188 GBV_ILN_2232 GBV_ILN_2336 GBV_ILN_2446 GBV_ILN_2470 GBV_ILN_2472 GBV_ILN_2507 GBV_ILN_2522 GBV_ILN_2548 GBV_ILN_4035 GBV_ILN_4037 GBV_ILN_4046 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4242 GBV_ILN_4246 GBV_ILN_4249 GBV_ILN_4251 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_4326 GBV_ILN_4333 GBV_ILN_4334 GBV_ILN_4335 GBV_ILN_4336 GBV_ILN_4338 GBV_ILN_4393 GBV_ILN_4700 AR 92 2013 1-2 01 01 3-16 |
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10.1007/BF03404659 doi (DE-627)SPR038612453 (SPR)BF03404659-e DE-627 ger DE-627 rakwb eng Mahmood, S. verfasserin aut Numerical Design of Leading Edge Flow Control over Swept High-Lift Airfoil 2013 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier © AIDAA Associazione Italiana di Aeronautica e Astronautica 2013 Abstract The present paper presents the numerical design of a leading edge flow control methodology over a swept two-element high-lift airfoil using steady state blowing through vortex generator jets. In baseline cases without flow control a turbulent leading-edge type of stall has been observed, therefore the vortex generator jets are applied at the leading edge of the airfoil to prevent separations and thus increase maximum lift and maximum angle of attack, respectively. The design of the flow control setup involves the variation of several geometrical and operational key parameters of the vortex generator jets, such as the pitch angle, skew angle, blowing ratio, sense of rotation and spanwise spacing of two adjacent jets. The results show that the numerical design of leading edge flow control is feasible for such wing arrangement. They show a significant degree of stall suppression over the swept high-lift airfoil. Scholz, P. aut Radespiel, R. aut Enthalten in Aerotecnica missili & spazio [Cham] : Springer International Publishing, 2001 92(2013), 1-2 vom: 01. Jan., Seite 3-16 (DE-627)1047764040 (DE-600)2960384-5 2524-6968 nnns volume:92 year:2013 number:1-2 day:01 month:01 pages:3-16 https://dx.doi.org/10.1007/BF03404659 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_SPRINGER GBV_ILN_11 GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_32 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_74 GBV_ILN_90 GBV_ILN_95 GBV_ILN_100 GBV_ILN_105 GBV_ILN_110 GBV_ILN_138 GBV_ILN_150 GBV_ILN_151 GBV_ILN_161 GBV_ILN_170 GBV_ILN_171 GBV_ILN_187 GBV_ILN_213 GBV_ILN_224 GBV_ILN_230 GBV_ILN_250 GBV_ILN_281 GBV_ILN_285 GBV_ILN_293 GBV_ILN_370 GBV_ILN_602 GBV_ILN_636 GBV_ILN_702 GBV_ILN_2001 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2006 GBV_ILN_2007 GBV_ILN_2008 GBV_ILN_2009 GBV_ILN_2010 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2026 GBV_ILN_2027 GBV_ILN_2031 GBV_ILN_2034 GBV_ILN_2037 GBV_ILN_2038 GBV_ILN_2039 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2055 GBV_ILN_2057 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2088 GBV_ILN_2093 GBV_ILN_2106 GBV_ILN_2107 GBV_ILN_2108 GBV_ILN_2110 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2118 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2144 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2188 GBV_ILN_2232 GBV_ILN_2336 GBV_ILN_2446 GBV_ILN_2470 GBV_ILN_2472 GBV_ILN_2507 GBV_ILN_2522 GBV_ILN_2548 GBV_ILN_4035 GBV_ILN_4037 GBV_ILN_4046 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4242 GBV_ILN_4246 GBV_ILN_4249 GBV_ILN_4251 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_4326 GBV_ILN_4333 GBV_ILN_4334 GBV_ILN_4335 GBV_ILN_4336 GBV_ILN_4338 GBV_ILN_4393 GBV_ILN_4700 AR 92 2013 1-2 01 01 3-16 |
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10.1007/BF03404659 doi (DE-627)SPR038612453 (SPR)BF03404659-e DE-627 ger DE-627 rakwb eng Mahmood, S. verfasserin aut Numerical Design of Leading Edge Flow Control over Swept High-Lift Airfoil 2013 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier © AIDAA Associazione Italiana di Aeronautica e Astronautica 2013 Abstract The present paper presents the numerical design of a leading edge flow control methodology over a swept two-element high-lift airfoil using steady state blowing through vortex generator jets. In baseline cases without flow control a turbulent leading-edge type of stall has been observed, therefore the vortex generator jets are applied at the leading edge of the airfoil to prevent separations and thus increase maximum lift and maximum angle of attack, respectively. The design of the flow control setup involves the variation of several geometrical and operational key parameters of the vortex generator jets, such as the pitch angle, skew angle, blowing ratio, sense of rotation and spanwise spacing of two adjacent jets. The results show that the numerical design of leading edge flow control is feasible for such wing arrangement. They show a significant degree of stall suppression over the swept high-lift airfoil. Scholz, P. aut Radespiel, R. aut Enthalten in Aerotecnica missili & spazio [Cham] : Springer International Publishing, 2001 92(2013), 1-2 vom: 01. Jan., Seite 3-16 (DE-627)1047764040 (DE-600)2960384-5 2524-6968 nnns volume:92 year:2013 number:1-2 day:01 month:01 pages:3-16 https://dx.doi.org/10.1007/BF03404659 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_SPRINGER GBV_ILN_11 GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_32 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_74 GBV_ILN_90 GBV_ILN_95 GBV_ILN_100 GBV_ILN_105 GBV_ILN_110 GBV_ILN_138 GBV_ILN_150 GBV_ILN_151 GBV_ILN_161 GBV_ILN_170 GBV_ILN_171 GBV_ILN_187 GBV_ILN_213 GBV_ILN_224 GBV_ILN_230 GBV_ILN_250 GBV_ILN_281 GBV_ILN_285 GBV_ILN_293 GBV_ILN_370 GBV_ILN_602 GBV_ILN_636 GBV_ILN_702 GBV_ILN_2001 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2006 GBV_ILN_2007 GBV_ILN_2008 GBV_ILN_2009 GBV_ILN_2010 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2026 GBV_ILN_2027 GBV_ILN_2031 GBV_ILN_2034 GBV_ILN_2037 GBV_ILN_2038 GBV_ILN_2039 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2055 GBV_ILN_2057 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2088 GBV_ILN_2093 GBV_ILN_2106 GBV_ILN_2107 GBV_ILN_2108 GBV_ILN_2110 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2118 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2144 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2188 GBV_ILN_2232 GBV_ILN_2336 GBV_ILN_2446 GBV_ILN_2470 GBV_ILN_2472 GBV_ILN_2507 GBV_ILN_2522 GBV_ILN_2548 GBV_ILN_4035 GBV_ILN_4037 GBV_ILN_4046 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4242 GBV_ILN_4246 GBV_ILN_4249 GBV_ILN_4251 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_4326 GBV_ILN_4333 GBV_ILN_4334 GBV_ILN_4335 GBV_ILN_4336 GBV_ILN_4338 GBV_ILN_4393 GBV_ILN_4700 AR 92 2013 1-2 01 01 3-16 |
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10.1007/BF03404659 doi (DE-627)SPR038612453 (SPR)BF03404659-e DE-627 ger DE-627 rakwb eng Mahmood, S. verfasserin aut Numerical Design of Leading Edge Flow Control over Swept High-Lift Airfoil 2013 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier © AIDAA Associazione Italiana di Aeronautica e Astronautica 2013 Abstract The present paper presents the numerical design of a leading edge flow control methodology over a swept two-element high-lift airfoil using steady state blowing through vortex generator jets. In baseline cases without flow control a turbulent leading-edge type of stall has been observed, therefore the vortex generator jets are applied at the leading edge of the airfoil to prevent separations and thus increase maximum lift and maximum angle of attack, respectively. The design of the flow control setup involves the variation of several geometrical and operational key parameters of the vortex generator jets, such as the pitch angle, skew angle, blowing ratio, sense of rotation and spanwise spacing of two adjacent jets. The results show that the numerical design of leading edge flow control is feasible for such wing arrangement. They show a significant degree of stall suppression over the swept high-lift airfoil. Scholz, P. aut Radespiel, R. aut Enthalten in Aerotecnica missili & spazio [Cham] : Springer International Publishing, 2001 92(2013), 1-2 vom: 01. Jan., Seite 3-16 (DE-627)1047764040 (DE-600)2960384-5 2524-6968 nnns volume:92 year:2013 number:1-2 day:01 month:01 pages:3-16 https://dx.doi.org/10.1007/BF03404659 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_SPRINGER GBV_ILN_11 GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_32 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_74 GBV_ILN_90 GBV_ILN_95 GBV_ILN_100 GBV_ILN_105 GBV_ILN_110 GBV_ILN_138 GBV_ILN_150 GBV_ILN_151 GBV_ILN_161 GBV_ILN_170 GBV_ILN_171 GBV_ILN_187 GBV_ILN_213 GBV_ILN_224 GBV_ILN_230 GBV_ILN_250 GBV_ILN_281 GBV_ILN_285 GBV_ILN_293 GBV_ILN_370 GBV_ILN_602 GBV_ILN_636 GBV_ILN_702 GBV_ILN_2001 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2006 GBV_ILN_2007 GBV_ILN_2008 GBV_ILN_2009 GBV_ILN_2010 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2026 GBV_ILN_2027 GBV_ILN_2031 GBV_ILN_2034 GBV_ILN_2037 GBV_ILN_2038 GBV_ILN_2039 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2055 GBV_ILN_2057 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2088 GBV_ILN_2093 GBV_ILN_2106 GBV_ILN_2107 GBV_ILN_2108 GBV_ILN_2110 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2118 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2144 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2188 GBV_ILN_2232 GBV_ILN_2336 GBV_ILN_2446 GBV_ILN_2470 GBV_ILN_2472 GBV_ILN_2507 GBV_ILN_2522 GBV_ILN_2548 GBV_ILN_4035 GBV_ILN_4037 GBV_ILN_4046 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4242 GBV_ILN_4246 GBV_ILN_4249 GBV_ILN_4251 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_4326 GBV_ILN_4333 GBV_ILN_4334 GBV_ILN_4335 GBV_ILN_4336 GBV_ILN_4338 GBV_ILN_4393 GBV_ILN_4700 AR 92 2013 1-2 01 01 3-16 |
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10.1007/BF03404659 doi (DE-627)SPR038612453 (SPR)BF03404659-e DE-627 ger DE-627 rakwb eng Mahmood, S. verfasserin aut Numerical Design of Leading Edge Flow Control over Swept High-Lift Airfoil 2013 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier © AIDAA Associazione Italiana di Aeronautica e Astronautica 2013 Abstract The present paper presents the numerical design of a leading edge flow control methodology over a swept two-element high-lift airfoil using steady state blowing through vortex generator jets. In baseline cases without flow control a turbulent leading-edge type of stall has been observed, therefore the vortex generator jets are applied at the leading edge of the airfoil to prevent separations and thus increase maximum lift and maximum angle of attack, respectively. The design of the flow control setup involves the variation of several geometrical and operational key parameters of the vortex generator jets, such as the pitch angle, skew angle, blowing ratio, sense of rotation and spanwise spacing of two adjacent jets. The results show that the numerical design of leading edge flow control is feasible for such wing arrangement. They show a significant degree of stall suppression over the swept high-lift airfoil. Scholz, P. aut Radespiel, R. aut Enthalten in Aerotecnica missili & spazio [Cham] : Springer International Publishing, 2001 92(2013), 1-2 vom: 01. Jan., Seite 3-16 (DE-627)1047764040 (DE-600)2960384-5 2524-6968 nnns volume:92 year:2013 number:1-2 day:01 month:01 pages:3-16 https://dx.doi.org/10.1007/BF03404659 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_SPRINGER GBV_ILN_11 GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_32 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_74 GBV_ILN_90 GBV_ILN_95 GBV_ILN_100 GBV_ILN_105 GBV_ILN_110 GBV_ILN_138 GBV_ILN_150 GBV_ILN_151 GBV_ILN_161 GBV_ILN_170 GBV_ILN_171 GBV_ILN_187 GBV_ILN_213 GBV_ILN_224 GBV_ILN_230 GBV_ILN_250 GBV_ILN_281 GBV_ILN_285 GBV_ILN_293 GBV_ILN_370 GBV_ILN_602 GBV_ILN_636 GBV_ILN_702 GBV_ILN_2001 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2006 GBV_ILN_2007 GBV_ILN_2008 GBV_ILN_2009 GBV_ILN_2010 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2026 GBV_ILN_2027 GBV_ILN_2031 GBV_ILN_2034 GBV_ILN_2037 GBV_ILN_2038 GBV_ILN_2039 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2055 GBV_ILN_2057 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2088 GBV_ILN_2093 GBV_ILN_2106 GBV_ILN_2107 GBV_ILN_2108 GBV_ILN_2110 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2118 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2144 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2188 GBV_ILN_2232 GBV_ILN_2336 GBV_ILN_2446 GBV_ILN_2470 GBV_ILN_2472 GBV_ILN_2507 GBV_ILN_2522 GBV_ILN_2548 GBV_ILN_4035 GBV_ILN_4037 GBV_ILN_4046 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4242 GBV_ILN_4246 GBV_ILN_4249 GBV_ILN_4251 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_4326 GBV_ILN_4333 GBV_ILN_4334 GBV_ILN_4335 GBV_ILN_4336 GBV_ILN_4338 GBV_ILN_4393 GBV_ILN_4700 AR 92 2013 1-2 01 01 3-16 |
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numerical design of leading edge flow control over swept high-lift airfoil |
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Numerical Design of Leading Edge Flow Control over Swept High-Lift Airfoil |
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Abstract The present paper presents the numerical design of a leading edge flow control methodology over a swept two-element high-lift airfoil using steady state blowing through vortex generator jets. In baseline cases without flow control a turbulent leading-edge type of stall has been observed, therefore the vortex generator jets are applied at the leading edge of the airfoil to prevent separations and thus increase maximum lift and maximum angle of attack, respectively. The design of the flow control setup involves the variation of several geometrical and operational key parameters of the vortex generator jets, such as the pitch angle, skew angle, blowing ratio, sense of rotation and spanwise spacing of two adjacent jets. The results show that the numerical design of leading edge flow control is feasible for such wing arrangement. They show a significant degree of stall suppression over the swept high-lift airfoil. © AIDAA Associazione Italiana di Aeronautica e Astronautica 2013 |
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Abstract The present paper presents the numerical design of a leading edge flow control methodology over a swept two-element high-lift airfoil using steady state blowing through vortex generator jets. In baseline cases without flow control a turbulent leading-edge type of stall has been observed, therefore the vortex generator jets are applied at the leading edge of the airfoil to prevent separations and thus increase maximum lift and maximum angle of attack, respectively. The design of the flow control setup involves the variation of several geometrical and operational key parameters of the vortex generator jets, such as the pitch angle, skew angle, blowing ratio, sense of rotation and spanwise spacing of two adjacent jets. The results show that the numerical design of leading edge flow control is feasible for such wing arrangement. They show a significant degree of stall suppression over the swept high-lift airfoil. © AIDAA Associazione Italiana di Aeronautica e Astronautica 2013 |
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Abstract The present paper presents the numerical design of a leading edge flow control methodology over a swept two-element high-lift airfoil using steady state blowing through vortex generator jets. In baseline cases without flow control a turbulent leading-edge type of stall has been observed, therefore the vortex generator jets are applied at the leading edge of the airfoil to prevent separations and thus increase maximum lift and maximum angle of attack, respectively. The design of the flow control setup involves the variation of several geometrical and operational key parameters of the vortex generator jets, such as the pitch angle, skew angle, blowing ratio, sense of rotation and spanwise spacing of two adjacent jets. The results show that the numerical design of leading edge flow control is feasible for such wing arrangement. They show a significant degree of stall suppression over the swept high-lift airfoil. © AIDAA Associazione Italiana di Aeronautica e Astronautica 2013 |
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