Effects of bevelled nozzles on standoff shocks in supersonic impinging jets

Moderately under-expanded jets issuing from a circular baseline and two bevelled circular nozzles impinging upon a perpendicular flat plate were experimentally studied. The effects of nozzle-pressure-ratio and separation distance variations on the standoff shock formations were investigated with sch...
Ausführliche Beschreibung

Gespeichert in:

Autor*in:	Lim, H.D. [verfasserIn] New, T.H. [verfasserIn] Mariani, R. [verfasserIn] Cui, Y.D. [verfasserIn]

Format:	E-Artikel
Sprache:	Englisch

Erschienen:	2019

Schlagwörter:	Schlieren Standoff shocks Unsteady shocks Shock reconstruction Supersonic jets Impinging jets

Übergeordnetes Werk:	Enthalten in: Aerospace science and technology - Amsterdam [u.a.] : Elsevier Science, 1997, 94
Übergeordnetes Werk:	volume:94

DOI / URN:	10.1016/j.ast.2019.105371

Katalog-ID:	ELV003005232

Internformat


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100	1		\|a Lim, H.D. \|e verfasserin \|4 aut
245	1	0	\|a Effects of bevelled nozzles on standoff shocks in supersonic impinging jets
264		1	\|c 2019
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337			\|a Computermedien \|b c \|2 rdamedia
338			\|a Online-Ressource \|b cr \|2 rdacarrier
520			\|a Moderately under-expanded jets issuing from a circular baseline and two bevelled circular nozzles impinging upon a perpendicular flat plate were experimentally studied. The effects of nozzle-pressure-ratio and separation distance variations on the standoff shock formations were investigated with schlieren visualizations and a visual hull based three-dimensional (3D) shock reconstruction technique to provide deeper insights into their 3D features. Across all flow configurations arising from the different combinations of these parameters, results indicated that the bevelled nozzles are effective in introducing asymmetry to the standoff shock geometries. Depending on the exact flow configuration, standoff shock locations may also undergo significant upstream displacements. In particular, the single-bevelled nozzle produces highly unsteady standoff shocks with asymmetric oscillation amplitudes along both side of the nozzle lip regions. Changes to the standoff shock key characteristics were observed to be sensitive towards the jet shock structures and reflection point modified by the bevelled nozzle exits. In particular, the strength and relative position of the reflection point are identified as the major contributing factors influencing the upstream static pressure distribution of the standoff shock, hence leading to the observed changes in the standoff shock behaviour.
650		4	\|a Schlieren
650		4	\|a Standoff shocks
650		4	\|a Unsteady shocks
650		4	\|a Shock reconstruction
650		4	\|a Supersonic jets
650		4	\|a Impinging jets
700	1		\|a New, T.H. \|e verfasserin \|4 aut
700	1		\|a Mariani, R. \|e verfasserin \|4 aut
700	1		\|a Cui, Y.D. \|e verfasserin \|4 aut
773	0	8	\|i Enthalten in \|t Aerospace science and technology \|d Amsterdam [u.a.] : Elsevier Science, 1997 \|g 94 \|h Online-Ressource \|w (DE-627)320521486 \|w (DE-600)2014638-3 \|w (DE-576)255630425 \|x 1626-3219 \|7 nnns
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912			\|a GBV_ILN_63
912			\|a GBV_ILN_65
912			\|a GBV_ILN_69
912			\|a GBV_ILN_70
912			\|a GBV_ILN_73
912			\|a GBV_ILN_74
912			\|a GBV_ILN_90
912			\|a GBV_ILN_95
912			\|a GBV_ILN_100
912			\|a GBV_ILN_105
912			\|a GBV_ILN_110
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912			\|a GBV_ILN_224
912			\|a GBV_ILN_370
912			\|a GBV_ILN_602
912			\|a GBV_ILN_702
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912			\|a GBV_ILN_2004
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912			\|a GBV_ILN_2021
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912			\|a GBV_ILN_2048
912			\|a GBV_ILN_2049
912			\|a GBV_ILN_2050
912			\|a GBV_ILN_2056
912			\|a GBV_ILN_2059
912			\|a GBV_ILN_2061
912			\|a GBV_ILN_2064
912			\|a GBV_ILN_2065
912			\|a GBV_ILN_2068
912			\|a GBV_ILN_2088
912			\|a GBV_ILN_2111
912			\|a GBV_ILN_2112
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936	b	k	\|a 55.50 \|j Luftfahrzeugtechnik
936	b	k	\|a 55.60 \|j Raumfahrttechnik
936	b	k	\|a 55.60 \|j Raumfahrttechnik
951			\|a AR
952			\|d 94

Indexfelder

author_variant	h l hl t n tn r m rm y c yc
matchkey_str	article:16263219:2019----::fetobvlenzlsntnofhcsnues
hierarchy_sort_str	2019
bklnumber	55.50 55.60
publishDate	2019
allfields	10.1016/j.ast.2019.105371 doi (DE-627)ELV003005232 (ELSEVIER)S1270-9638(19)30465-1 DE-627 ger DE-627 rda eng 620 DE-600 55.50 bkl 55.60 bkl 55.60 bkl Lim, H.D. verfasserin aut Effects of bevelled nozzles on standoff shocks in supersonic impinging jets 2019 nicht spezifiziert zzz rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier Moderately under-expanded jets issuing from a circular baseline and two bevelled circular nozzles impinging upon a perpendicular flat plate were experimentally studied. The effects of nozzle-pressure-ratio and separation distance variations on the standoff shock formations were investigated with schlieren visualizations and a visual hull based three-dimensional (3D) shock reconstruction technique to provide deeper insights into their 3D features. Across all flow configurations arising from the different combinations of these parameters, results indicated that the bevelled nozzles are effective in introducing asymmetry to the standoff shock geometries. Depending on the exact flow configuration, standoff shock locations may also undergo significant upstream displacements. In particular, the single-bevelled nozzle produces highly unsteady standoff shocks with asymmetric oscillation amplitudes along both side of the nozzle lip regions. Changes to the standoff shock key characteristics were observed to be sensitive towards the jet shock structures and reflection point modified by the bevelled nozzle exits. In particular, the strength and relative position of the reflection point are identified as the major contributing factors influencing the upstream static pressure distribution of the standoff shock, hence leading to the observed changes in the standoff shock behaviour. Schlieren Standoff shocks Unsteady shocks Shock reconstruction Supersonic jets Impinging jets New, T.H. verfasserin aut Mariani, R. verfasserin aut Cui, Y.D. verfasserin aut Enthalten in Aerospace science and technology Amsterdam [u.a.] : Elsevier Science, 1997 94 Online-Ressource (DE-627)320521486 (DE-600)2014638-3 (DE-576)255630425 1626-3219 nnns volume:94 GBV_USEFLAG_U SYSFLAG_U GBV_ELV SSG-OPC-AST GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_32 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_150 GBV_ILN_151 GBV_ILN_224 GBV_ILN_370 GBV_ILN_602 GBV_ILN_702 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2006 GBV_ILN_2008 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2027 GBV_ILN_2034 GBV_ILN_2038 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2056 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2088 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2118 GBV_ILN_2122 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2190 GBV_ILN_2336 GBV_ILN_2470 GBV_ILN_2507 GBV_ILN_2522 GBV_ILN_4035 GBV_ILN_4037 GBV_ILN_4046 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4126 GBV_ILN_4242 GBV_ILN_4251 GBV_ILN_4305 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_4338 GBV_ILN_4393 55.50 Luftfahrzeugtechnik 55.60 Raumfahrttechnik 55.60 Raumfahrttechnik AR 94
spelling	10.1016/j.ast.2019.105371 doi (DE-627)ELV003005232 (ELSEVIER)S1270-9638(19)30465-1 DE-627 ger DE-627 rda eng 620 DE-600 55.50 bkl 55.60 bkl 55.60 bkl Lim, H.D. verfasserin aut Effects of bevelled nozzles on standoff shocks in supersonic impinging jets 2019 nicht spezifiziert zzz rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier Moderately under-expanded jets issuing from a circular baseline and two bevelled circular nozzles impinging upon a perpendicular flat plate were experimentally studied. The effects of nozzle-pressure-ratio and separation distance variations on the standoff shock formations were investigated with schlieren visualizations and a visual hull based three-dimensional (3D) shock reconstruction technique to provide deeper insights into their 3D features. Across all flow configurations arising from the different combinations of these parameters, results indicated that the bevelled nozzles are effective in introducing asymmetry to the standoff shock geometries. Depending on the exact flow configuration, standoff shock locations may also undergo significant upstream displacements. In particular, the single-bevelled nozzle produces highly unsteady standoff shocks with asymmetric oscillation amplitudes along both side of the nozzle lip regions. Changes to the standoff shock key characteristics were observed to be sensitive towards the jet shock structures and reflection point modified by the bevelled nozzle exits. In particular, the strength and relative position of the reflection point are identified as the major contributing factors influencing the upstream static pressure distribution of the standoff shock, hence leading to the observed changes in the standoff shock behaviour. Schlieren Standoff shocks Unsteady shocks Shock reconstruction Supersonic jets Impinging jets New, T.H. verfasserin aut Mariani, R. verfasserin aut Cui, Y.D. verfasserin aut Enthalten in Aerospace science and technology Amsterdam [u.a.] : Elsevier Science, 1997 94 Online-Ressource (DE-627)320521486 (DE-600)2014638-3 (DE-576)255630425 1626-3219 nnns volume:94 GBV_USEFLAG_U SYSFLAG_U GBV_ELV SSG-OPC-AST GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_32 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_150 GBV_ILN_151 GBV_ILN_224 GBV_ILN_370 GBV_ILN_602 GBV_ILN_702 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2006 GBV_ILN_2008 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2027 GBV_ILN_2034 GBV_ILN_2038 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2056 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2088 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2118 GBV_ILN_2122 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2190 GBV_ILN_2336 GBV_ILN_2470 GBV_ILN_2507 GBV_ILN_2522 GBV_ILN_4035 GBV_ILN_4037 GBV_ILN_4046 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4126 GBV_ILN_4242 GBV_ILN_4251 GBV_ILN_4305 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_4338 GBV_ILN_4393 55.50 Luftfahrzeugtechnik 55.60 Raumfahrttechnik 55.60 Raumfahrttechnik AR 94
allfields_unstemmed	10.1016/j.ast.2019.105371 doi (DE-627)ELV003005232 (ELSEVIER)S1270-9638(19)30465-1 DE-627 ger DE-627 rda eng 620 DE-600 55.50 bkl 55.60 bkl 55.60 bkl Lim, H.D. verfasserin aut Effects of bevelled nozzles on standoff shocks in supersonic impinging jets 2019 nicht spezifiziert zzz rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier Moderately under-expanded jets issuing from a circular baseline and two bevelled circular nozzles impinging upon a perpendicular flat plate were experimentally studied. The effects of nozzle-pressure-ratio and separation distance variations on the standoff shock formations were investigated with schlieren visualizations and a visual hull based three-dimensional (3D) shock reconstruction technique to provide deeper insights into their 3D features. Across all flow configurations arising from the different combinations of these parameters, results indicated that the bevelled nozzles are effective in introducing asymmetry to the standoff shock geometries. Depending on the exact flow configuration, standoff shock locations may also undergo significant upstream displacements. In particular, the single-bevelled nozzle produces highly unsteady standoff shocks with asymmetric oscillation amplitudes along both side of the nozzle lip regions. Changes to the standoff shock key characteristics were observed to be sensitive towards the jet shock structures and reflection point modified by the bevelled nozzle exits. In particular, the strength and relative position of the reflection point are identified as the major contributing factors influencing the upstream static pressure distribution of the standoff shock, hence leading to the observed changes in the standoff shock behaviour. Schlieren Standoff shocks Unsteady shocks Shock reconstruction Supersonic jets Impinging jets New, T.H. verfasserin aut Mariani, R. verfasserin aut Cui, Y.D. verfasserin aut Enthalten in Aerospace science and technology Amsterdam [u.a.] : Elsevier Science, 1997 94 Online-Ressource (DE-627)320521486 (DE-600)2014638-3 (DE-576)255630425 1626-3219 nnns volume:94 GBV_USEFLAG_U SYSFLAG_U GBV_ELV SSG-OPC-AST GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_32 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_150 GBV_ILN_151 GBV_ILN_224 GBV_ILN_370 GBV_ILN_602 GBV_ILN_702 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2006 GBV_ILN_2008 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2027 GBV_ILN_2034 GBV_ILN_2038 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2056 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2088 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2118 GBV_ILN_2122 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2190 GBV_ILN_2336 GBV_ILN_2470 GBV_ILN_2507 GBV_ILN_2522 GBV_ILN_4035 GBV_ILN_4037 GBV_ILN_4046 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4126 GBV_ILN_4242 GBV_ILN_4251 GBV_ILN_4305 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_4338 GBV_ILN_4393 55.50 Luftfahrzeugtechnik 55.60 Raumfahrttechnik 55.60 Raumfahrttechnik AR 94
allfieldsGer	10.1016/j.ast.2019.105371 doi (DE-627)ELV003005232 (ELSEVIER)S1270-9638(19)30465-1 DE-627 ger DE-627 rda eng 620 DE-600 55.50 bkl 55.60 bkl 55.60 bkl Lim, H.D. verfasserin aut Effects of bevelled nozzles on standoff shocks in supersonic impinging jets 2019 nicht spezifiziert zzz rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier Moderately under-expanded jets issuing from a circular baseline and two bevelled circular nozzles impinging upon a perpendicular flat plate were experimentally studied. The effects of nozzle-pressure-ratio and separation distance variations on the standoff shock formations were investigated with schlieren visualizations and a visual hull based three-dimensional (3D) shock reconstruction technique to provide deeper insights into their 3D features. Across all flow configurations arising from the different combinations of these parameters, results indicated that the bevelled nozzles are effective in introducing asymmetry to the standoff shock geometries. Depending on the exact flow configuration, standoff shock locations may also undergo significant upstream displacements. In particular, the single-bevelled nozzle produces highly unsteady standoff shocks with asymmetric oscillation amplitudes along both side of the nozzle lip regions. Changes to the standoff shock key characteristics were observed to be sensitive towards the jet shock structures and reflection point modified by the bevelled nozzle exits. In particular, the strength and relative position of the reflection point are identified as the major contributing factors influencing the upstream static pressure distribution of the standoff shock, hence leading to the observed changes in the standoff shock behaviour. Schlieren Standoff shocks Unsteady shocks Shock reconstruction Supersonic jets Impinging jets New, T.H. verfasserin aut Mariani, R. verfasserin aut Cui, Y.D. verfasserin aut Enthalten in Aerospace science and technology Amsterdam [u.a.] : Elsevier Science, 1997 94 Online-Ressource (DE-627)320521486 (DE-600)2014638-3 (DE-576)255630425 1626-3219 nnns volume:94 GBV_USEFLAG_U SYSFLAG_U GBV_ELV SSG-OPC-AST GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_32 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_150 GBV_ILN_151 GBV_ILN_224 GBV_ILN_370 GBV_ILN_602 GBV_ILN_702 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2006 GBV_ILN_2008 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2027 GBV_ILN_2034 GBV_ILN_2038 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2056 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2088 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2118 GBV_ILN_2122 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2190 GBV_ILN_2336 GBV_ILN_2470 GBV_ILN_2507 GBV_ILN_2522 GBV_ILN_4035 GBV_ILN_4037 GBV_ILN_4046 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4126 GBV_ILN_4242 GBV_ILN_4251 GBV_ILN_4305 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_4338 GBV_ILN_4393 55.50 Luftfahrzeugtechnik 55.60 Raumfahrttechnik 55.60 Raumfahrttechnik AR 94
allfieldsSound	10.1016/j.ast.2019.105371 doi (DE-627)ELV003005232 (ELSEVIER)S1270-9638(19)30465-1 DE-627 ger DE-627 rda eng 620 DE-600 55.50 bkl 55.60 bkl 55.60 bkl Lim, H.D. verfasserin aut Effects of bevelled nozzles on standoff shocks in supersonic impinging jets 2019 nicht spezifiziert zzz rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier Moderately under-expanded jets issuing from a circular baseline and two bevelled circular nozzles impinging upon a perpendicular flat plate were experimentally studied. The effects of nozzle-pressure-ratio and separation distance variations on the standoff shock formations were investigated with schlieren visualizations and a visual hull based three-dimensional (3D) shock reconstruction technique to provide deeper insights into their 3D features. Across all flow configurations arising from the different combinations of these parameters, results indicated that the bevelled nozzles are effective in introducing asymmetry to the standoff shock geometries. Depending on the exact flow configuration, standoff shock locations may also undergo significant upstream displacements. In particular, the single-bevelled nozzle produces highly unsteady standoff shocks with asymmetric oscillation amplitudes along both side of the nozzle lip regions. Changes to the standoff shock key characteristics were observed to be sensitive towards the jet shock structures and reflection point modified by the bevelled nozzle exits. In particular, the strength and relative position of the reflection point are identified as the major contributing factors influencing the upstream static pressure distribution of the standoff shock, hence leading to the observed changes in the standoff shock behaviour. Schlieren Standoff shocks Unsteady shocks Shock reconstruction Supersonic jets Impinging jets New, T.H. verfasserin aut Mariani, R. verfasserin aut Cui, Y.D. verfasserin aut Enthalten in Aerospace science and technology Amsterdam [u.a.] : Elsevier Science, 1997 94 Online-Ressource (DE-627)320521486 (DE-600)2014638-3 (DE-576)255630425 1626-3219 nnns volume:94 GBV_USEFLAG_U SYSFLAG_U GBV_ELV SSG-OPC-AST GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_32 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_150 GBV_ILN_151 GBV_ILN_224 GBV_ILN_370 GBV_ILN_602 GBV_ILN_702 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2006 GBV_ILN_2008 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2027 GBV_ILN_2034 GBV_ILN_2038 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2056 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2088 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2118 GBV_ILN_2122 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2190 GBV_ILN_2336 GBV_ILN_2470 GBV_ILN_2507 GBV_ILN_2522 GBV_ILN_4035 GBV_ILN_4037 GBV_ILN_4046 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4126 GBV_ILN_4242 GBV_ILN_4251 GBV_ILN_4305 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_4338 GBV_ILN_4393 55.50 Luftfahrzeugtechnik 55.60 Raumfahrttechnik 55.60 Raumfahrttechnik AR 94
language	English
source	Enthalten in Aerospace science and technology 94 volume:94
sourceStr	Enthalten in Aerospace science and technology 94 volume:94
format_phy_str_mv	Article
bklname	Luftfahrzeugtechnik Raumfahrttechnik
institution	findex.gbv.de
topic_facet	Schlieren Standoff shocks Unsteady shocks Shock reconstruction Supersonic jets Impinging jets
dewey-raw	620
isfreeaccess_bool	false
container_title	Aerospace science and technology
authorswithroles_txt_mv	Lim, H.D. @@aut@@ New, T.H. @@aut@@ Mariani, R. @@aut@@ Cui, Y.D. @@aut@@
publishDateDaySort_date	2019-01-01T00:00:00Z
hierarchy_top_id	320521486
dewey-sort	3620
id	ELV003005232
language_de	englisch
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author	Lim, H.D.
spellingShingle	Lim, H.D. ddc 620 bkl 55.50 bkl 55.60 misc Schlieren misc Standoff shocks misc Unsteady shocks misc Shock reconstruction misc Supersonic jets misc Impinging jets Effects of bevelled nozzles on standoff shocks in supersonic impinging jets
authorStr	Lim, H.D.
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topic_title	620 DE-600 55.50 bkl 55.60 bkl Effects of bevelled nozzles on standoff shocks in supersonic impinging jets Schlieren Standoff shocks Unsteady shocks Shock reconstruction Supersonic jets Impinging jets
topic	ddc 620 bkl 55.50 bkl 55.60 misc Schlieren misc Standoff shocks misc Unsteady shocks misc Shock reconstruction misc Supersonic jets misc Impinging jets
topic_unstemmed	ddc 620 bkl 55.50 bkl 55.60 misc Schlieren misc Standoff shocks misc Unsteady shocks misc Shock reconstruction misc Supersonic jets misc Impinging jets
topic_browse	ddc 620 bkl 55.50 bkl 55.60 misc Schlieren misc Standoff shocks misc Unsteady shocks misc Shock reconstruction misc Supersonic jets misc Impinging jets
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title	Effects of bevelled nozzles on standoff shocks in supersonic impinging jets
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title_full	Effects of bevelled nozzles on standoff shocks in supersonic impinging jets
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author_browse	Lim, H.D. New, T.H. Mariani, R. Cui, Y.D.
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author-letter	Lim, H.D.
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title_sort	effects of bevelled nozzles on standoff shocks in supersonic impinging jets
title_auth	Effects of bevelled nozzles on standoff shocks in supersonic impinging jets
abstract	Moderately under-expanded jets issuing from a circular baseline and two bevelled circular nozzles impinging upon a perpendicular flat plate were experimentally studied. The effects of nozzle-pressure-ratio and separation distance variations on the standoff shock formations were investigated with schlieren visualizations and a visual hull based three-dimensional (3D) shock reconstruction technique to provide deeper insights into their 3D features. Across all flow configurations arising from the different combinations of these parameters, results indicated that the bevelled nozzles are effective in introducing asymmetry to the standoff shock geometries. Depending on the exact flow configuration, standoff shock locations may also undergo significant upstream displacements. In particular, the single-bevelled nozzle produces highly unsteady standoff shocks with asymmetric oscillation amplitudes along both side of the nozzle lip regions. Changes to the standoff shock key characteristics were observed to be sensitive towards the jet shock structures and reflection point modified by the bevelled nozzle exits. In particular, the strength and relative position of the reflection point are identified as the major contributing factors influencing the upstream static pressure distribution of the standoff shock, hence leading to the observed changes in the standoff shock behaviour.
abstractGer	Moderately under-expanded jets issuing from a circular baseline and two bevelled circular nozzles impinging upon a perpendicular flat plate were experimentally studied. The effects of nozzle-pressure-ratio and separation distance variations on the standoff shock formations were investigated with schlieren visualizations and a visual hull based three-dimensional (3D) shock reconstruction technique to provide deeper insights into their 3D features. Across all flow configurations arising from the different combinations of these parameters, results indicated that the bevelled nozzles are effective in introducing asymmetry to the standoff shock geometries. Depending on the exact flow configuration, standoff shock locations may also undergo significant upstream displacements. In particular, the single-bevelled nozzle produces highly unsteady standoff shocks with asymmetric oscillation amplitudes along both side of the nozzle lip regions. Changes to the standoff shock key characteristics were observed to be sensitive towards the jet shock structures and reflection point modified by the bevelled nozzle exits. In particular, the strength and relative position of the reflection point are identified as the major contributing factors influencing the upstream static pressure distribution of the standoff shock, hence leading to the observed changes in the standoff shock behaviour.
abstract_unstemmed	Moderately under-expanded jets issuing from a circular baseline and two bevelled circular nozzles impinging upon a perpendicular flat plate were experimentally studied. The effects of nozzle-pressure-ratio and separation distance variations on the standoff shock formations were investigated with schlieren visualizations and a visual hull based three-dimensional (3D) shock reconstruction technique to provide deeper insights into their 3D features. Across all flow configurations arising from the different combinations of these parameters, results indicated that the bevelled nozzles are effective in introducing asymmetry to the standoff shock geometries. Depending on the exact flow configuration, standoff shock locations may also undergo significant upstream displacements. In particular, the single-bevelled nozzle produces highly unsteady standoff shocks with asymmetric oscillation amplitudes along both side of the nozzle lip regions. Changes to the standoff shock key characteristics were observed to be sensitive towards the jet shock structures and reflection point modified by the bevelled nozzle exits. In particular, the strength and relative position of the reflection point are identified as the major contributing factors influencing the upstream static pressure distribution of the standoff shock, hence leading to the observed changes in the standoff shock behaviour.
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title_short	Effects of bevelled nozzles on standoff shocks in supersonic impinging jets
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author2	New, T.H. Mariani, R. Cui, Y.D.
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up_date	2024-07-06T18:10:42.672Z
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Effects of bevelled nozzles on standoff shocks in supersonic impinging jets

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