Visualization of over-expanded supersonic wall-jet

An experimental study has been conducted to understand the near flowfield of an over-expanded supersonic wall-jet (Mach number = 1.7 and unit Reynolds number = 2.13 × 10...
Ausführliche Beschreibung

Gespeichert in:

Autor*in:	S, Vaisakh [verfasserIn] Muruganandam, T.M. [verfasserIn]

Format:	E-Artikel
Sprache:	Englisch

Erschienen:	2021

Schlagwörter:	Supersonic flow Wall-jet Shock-wave/boundary-layer interaction Oil flow visualization Infrared thermography

Übergeordnetes Werk:	Enthalten in: Aerospace science and technology - Amsterdam [u.a.] : Elsevier Science, 1997, 112
Übergeordnetes Werk:	volume:112

DOI / URN:	10.1016/j.ast.2021.106617

Katalog-ID:	ELV005805228

Internformat


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245	1	0	\|a Visualization of over-expanded supersonic wall-jet
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520			\|a An experimental study has been conducted to understand the near flowfield of an over-expanded supersonic wall-jet (Mach number = 1.7 and unit Reynolds number = 2.13 × 10 7 m − 1 ). The primary and secondary shocks of both free-jet and wall-jet have been studied in detail. The flow features are captured with shadowgraphy, oil flow visualization and infrared thermography. Since both oil flow visualization and infrared thermography have been used for surface flow visualization, a comparative study is also performed between oil flow visualization and infrared thermography. This reveals their ability to capture supersonic surface flow features like shock-wave/boundary-layer interaction, expansion-wave/boundary-layer interaction, separation bubble and shear layer growth on the wall. The merits and demerits of the two methods are listed.
650		4	\|a Supersonic flow
650		4	\|a Wall-jet
650		4	\|a Shock-wave/boundary-layer interaction
650		4	\|a Oil flow visualization
650		4	\|a Infrared thermography
700	1		\|a Muruganandam, T.M. \|e verfasserin \|4 aut
773	0	8	\|i Enthalten in \|t Aerospace science and technology \|d Amsterdam [u.a.] : Elsevier Science, 1997 \|g 112 \|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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936	b	k	\|a 55.50 \|j Luftfahrzeugtechnik
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publishDate	2021
allfields	10.1016/j.ast.2021.106617 doi (DE-627)ELV005805228 (ELSEVIER)S1270-9638(21)00127-9 DE-627 ger DE-627 rda eng 620 DE-600 55.50 bkl 55.60 bkl 55.60 bkl S, Vaisakh verfasserin (orcid)0000-0001-5537-1966 aut Visualization of over-expanded supersonic wall-jet 2021 nicht spezifiziert zzz rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier An experimental study has been conducted to understand the near flowfield of an over-expanded supersonic wall-jet (Mach number = 1.7 and unit Reynolds number = 2.13 × 10 7 m − 1 ). The primary and secondary shocks of both free-jet and wall-jet have been studied in detail. The flow features are captured with shadowgraphy, oil flow visualization and infrared thermography. Since both oil flow visualization and infrared thermography have been used for surface flow visualization, a comparative study is also performed between oil flow visualization and infrared thermography. This reveals their ability to capture supersonic surface flow features like shock-wave/boundary-layer interaction, expansion-wave/boundary-layer interaction, separation bubble and shear layer growth on the wall. The merits and demerits of the two methods are listed. Supersonic flow Wall-jet Shock-wave/boundary-layer interaction Oil flow visualization Infrared thermography Muruganandam, T.M. verfasserin aut Enthalten in Aerospace science and technology Amsterdam [u.a.] : Elsevier Science, 1997 112 Online-Ressource (DE-627)320521486 (DE-600)2014638-3 (DE-576)255630425 1626-3219 nnns volume:112 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 112
spelling	10.1016/j.ast.2021.106617 doi (DE-627)ELV005805228 (ELSEVIER)S1270-9638(21)00127-9 DE-627 ger DE-627 rda eng 620 DE-600 55.50 bkl 55.60 bkl 55.60 bkl S, Vaisakh verfasserin (orcid)0000-0001-5537-1966 aut Visualization of over-expanded supersonic wall-jet 2021 nicht spezifiziert zzz rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier An experimental study has been conducted to understand the near flowfield of an over-expanded supersonic wall-jet (Mach number = 1.7 and unit Reynolds number = 2.13 × 10 7 m − 1 ). The primary and secondary shocks of both free-jet and wall-jet have been studied in detail. The flow features are captured with shadowgraphy, oil flow visualization and infrared thermography. Since both oil flow visualization and infrared thermography have been used for surface flow visualization, a comparative study is also performed between oil flow visualization and infrared thermography. This reveals their ability to capture supersonic surface flow features like shock-wave/boundary-layer interaction, expansion-wave/boundary-layer interaction, separation bubble and shear layer growth on the wall. The merits and demerits of the two methods are listed. Supersonic flow Wall-jet Shock-wave/boundary-layer interaction Oil flow visualization Infrared thermography Muruganandam, T.M. verfasserin aut Enthalten in Aerospace science and technology Amsterdam [u.a.] : Elsevier Science, 1997 112 Online-Ressource (DE-627)320521486 (DE-600)2014638-3 (DE-576)255630425 1626-3219 nnns volume:112 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 112
allfields_unstemmed	10.1016/j.ast.2021.106617 doi (DE-627)ELV005805228 (ELSEVIER)S1270-9638(21)00127-9 DE-627 ger DE-627 rda eng 620 DE-600 55.50 bkl 55.60 bkl 55.60 bkl S, Vaisakh verfasserin (orcid)0000-0001-5537-1966 aut Visualization of over-expanded supersonic wall-jet 2021 nicht spezifiziert zzz rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier An experimental study has been conducted to understand the near flowfield of an over-expanded supersonic wall-jet (Mach number = 1.7 and unit Reynolds number = 2.13 × 10 7 m − 1 ). The primary and secondary shocks of both free-jet and wall-jet have been studied in detail. The flow features are captured with shadowgraphy, oil flow visualization and infrared thermography. Since both oil flow visualization and infrared thermography have been used for surface flow visualization, a comparative study is also performed between oil flow visualization and infrared thermography. This reveals their ability to capture supersonic surface flow features like shock-wave/boundary-layer interaction, expansion-wave/boundary-layer interaction, separation bubble and shear layer growth on the wall. The merits and demerits of the two methods are listed. Supersonic flow Wall-jet Shock-wave/boundary-layer interaction Oil flow visualization Infrared thermography Muruganandam, T.M. verfasserin aut Enthalten in Aerospace science and technology Amsterdam [u.a.] : Elsevier Science, 1997 112 Online-Ressource (DE-627)320521486 (DE-600)2014638-3 (DE-576)255630425 1626-3219 nnns volume:112 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 112
allfieldsGer	10.1016/j.ast.2021.106617 doi (DE-627)ELV005805228 (ELSEVIER)S1270-9638(21)00127-9 DE-627 ger DE-627 rda eng 620 DE-600 55.50 bkl 55.60 bkl 55.60 bkl S, Vaisakh verfasserin (orcid)0000-0001-5537-1966 aut Visualization of over-expanded supersonic wall-jet 2021 nicht spezifiziert zzz rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier An experimental study has been conducted to understand the near flowfield of an over-expanded supersonic wall-jet (Mach number = 1.7 and unit Reynolds number = 2.13 × 10 7 m − 1 ). The primary and secondary shocks of both free-jet and wall-jet have been studied in detail. The flow features are captured with shadowgraphy, oil flow visualization and infrared thermography. Since both oil flow visualization and infrared thermography have been used for surface flow visualization, a comparative study is also performed between oil flow visualization and infrared thermography. This reveals their ability to capture supersonic surface flow features like shock-wave/boundary-layer interaction, expansion-wave/boundary-layer interaction, separation bubble and shear layer growth on the wall. The merits and demerits of the two methods are listed. Supersonic flow Wall-jet Shock-wave/boundary-layer interaction Oil flow visualization Infrared thermography Muruganandam, T.M. verfasserin aut Enthalten in Aerospace science and technology Amsterdam [u.a.] : Elsevier Science, 1997 112 Online-Ressource (DE-627)320521486 (DE-600)2014638-3 (DE-576)255630425 1626-3219 nnns volume:112 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 112
allfieldsSound	10.1016/j.ast.2021.106617 doi (DE-627)ELV005805228 (ELSEVIER)S1270-9638(21)00127-9 DE-627 ger DE-627 rda eng 620 DE-600 55.50 bkl 55.60 bkl 55.60 bkl S, Vaisakh verfasserin (orcid)0000-0001-5537-1966 aut Visualization of over-expanded supersonic wall-jet 2021 nicht spezifiziert zzz rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier An experimental study has been conducted to understand the near flowfield of an over-expanded supersonic wall-jet (Mach number = 1.7 and unit Reynolds number = 2.13 × 10 7 m − 1 ). The primary and secondary shocks of both free-jet and wall-jet have been studied in detail. The flow features are captured with shadowgraphy, oil flow visualization and infrared thermography. Since both oil flow visualization and infrared thermography have been used for surface flow visualization, a comparative study is also performed between oil flow visualization and infrared thermography. This reveals their ability to capture supersonic surface flow features like shock-wave/boundary-layer interaction, expansion-wave/boundary-layer interaction, separation bubble and shear layer growth on the wall. The merits and demerits of the two methods are listed. Supersonic flow Wall-jet Shock-wave/boundary-layer interaction Oil flow visualization Infrared thermography Muruganandam, T.M. verfasserin aut Enthalten in Aerospace science and technology Amsterdam [u.a.] : Elsevier Science, 1997 112 Online-Ressource (DE-627)320521486 (DE-600)2014638-3 (DE-576)255630425 1626-3219 nnns volume:112 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 112
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author	S, Vaisakh
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title	Visualization of over-expanded supersonic wall-jet
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author_browse	S, Vaisakh Muruganandam, T.M.
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doi_str_mv	10.1016/j.ast.2021.106617
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title_sort	visualization of over-expanded supersonic wall-jet
title_auth	Visualization of over-expanded supersonic wall-jet
abstract	An experimental study has been conducted to understand the near flowfield of an over-expanded supersonic wall-jet (Mach number = 1.7 and unit Reynolds number = 2.13 × 10 7 m − 1 ). The primary and secondary shocks of both free-jet and wall-jet have been studied in detail. The flow features are captured with shadowgraphy, oil flow visualization and infrared thermography. Since both oil flow visualization and infrared thermography have been used for surface flow visualization, a comparative study is also performed between oil flow visualization and infrared thermography. This reveals their ability to capture supersonic surface flow features like shock-wave/boundary-layer interaction, expansion-wave/boundary-layer interaction, separation bubble and shear layer growth on the wall. The merits and demerits of the two methods are listed.
abstractGer	An experimental study has been conducted to understand the near flowfield of an over-expanded supersonic wall-jet (Mach number = 1.7 and unit Reynolds number = 2.13 × 10 7 m − 1 ). The primary and secondary shocks of both free-jet and wall-jet have been studied in detail. The flow features are captured with shadowgraphy, oil flow visualization and infrared thermography. Since both oil flow visualization and infrared thermography have been used for surface flow visualization, a comparative study is also performed between oil flow visualization and infrared thermography. This reveals their ability to capture supersonic surface flow features like shock-wave/boundary-layer interaction, expansion-wave/boundary-layer interaction, separation bubble and shear layer growth on the wall. The merits and demerits of the two methods are listed.
abstract_unstemmed	An experimental study has been conducted to understand the near flowfield of an over-expanded supersonic wall-jet (Mach number = 1.7 and unit Reynolds number = 2.13 × 10 7 m − 1 ). The primary and secondary shocks of both free-jet and wall-jet have been studied in detail. The flow features are captured with shadowgraphy, oil flow visualization and infrared thermography. Since both oil flow visualization and infrared thermography have been used for surface flow visualization, a comparative study is also performed between oil flow visualization and infrared thermography. This reveals their ability to capture supersonic surface flow features like shock-wave/boundary-layer interaction, expansion-wave/boundary-layer interaction, separation bubble and shear layer growth on the wall. The merits and demerits of the two methods are listed.
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title_short	Visualization of over-expanded supersonic wall-jet
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doi_str	10.1016/j.ast.2021.106617
up_date	2024-07-06T19:13:21.559Z
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