Influence of small attack angles on the transition on the wing with the subsonic leading edge at M=2
The paper is devoted to an experimental study of laminar-turbulent transition in supersonic boundary layers on swept wings. The experiments were fulfilled in the low nose supersonic wind tunnel T-325 of Khristianovich Institute of Theoretical and Applied Mechanics on the models of a swept wing with...
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| creator | Semionov, N. V. Kosinov, A. D. Yermolaev, Yu. G. Kocharin, V. L. Shipul, S. A. Yatskikh, A. A. |
| description | The paper is devoted to an experimental study of laminar-turbulent transition in supersonic boundary layers on swept wings. The experiments were fulfilled in the low nose supersonic wind tunnel T-325 of Khristianovich Institute of Theoretical and Applied Mechanics on the models of a swept wing with a swept angle of 72° at Mach 2 which corresponds to a subsonic leading edge. The transition location was determined using a constant temperature hot-wire anemometer. A comparison of the influence of small angles of attack on the transition position with a model with a supersonic leading edge is shown. The transition to a wing model with a subsonic leading edge occurs earlier than on a wing model with a supersonic leading edge. The angle of attack has a significant effect on the position of the transition point from the laminar to turbulent flow. The data presented in the article are among the first results for a swept wing with a subsonic leading edge. |
| doi_str_mv | 10.1063/5.0028295 |
| format | Conference Proceeding |
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V. ; Kosinov, A. D. ; Yermolaev, Yu. G. ; Kocharin, V. L. ; Shipul, S. A. ; Yatskikh, A. A.</creator><contributor>Fomin, Vasily</contributor><creatorcontrib>Semionov, N. V. ; Kosinov, A. D. ; Yermolaev, Yu. G. ; Kocharin, V. L. ; Shipul, S. A. ; Yatskikh, A. A. ; Fomin, Vasily</creatorcontrib><description>The paper is devoted to an experimental study of laminar-turbulent transition in supersonic boundary layers on swept wings. The experiments were fulfilled in the low nose supersonic wind tunnel T-325 of Khristianovich Institute of Theoretical and Applied Mechanics on the models of a swept wing with a swept angle of 72° at Mach 2 which corresponds to a subsonic leading edge. The transition location was determined using a constant temperature hot-wire anemometer. A comparison of the influence of small angles of attack on the transition position with a model with a supersonic leading edge is shown. The transition to a wing model with a subsonic leading edge occurs earlier than on a wing model with a supersonic leading edge. The angle of attack has a significant effect on the position of the transition point from the laminar to turbulent flow. The data presented in the article are among the first results for a swept wing with a subsonic leading edge.</description><identifier>ISSN: 0094-243X</identifier><identifier>EISSN: 1551-7616</identifier><identifier>DOI: 10.1063/5.0028295</identifier><identifier>CODEN: APCPCS</identifier><language>eng</language><publisher>Melville: American Institute of Physics</publisher><subject>Angle of attack ; Boundary layer transition ; Computational fluid dynamics ; Laminar flow ; Supersonic boundary layers ; Supersonic wind tunnels ; Swept wings ; Transition points ; Turbulent boundary layer ; Turbulent flow</subject><ispartof>AIP Conference Proceedings, 2020, Vol.2288 (1)</ispartof><rights>Author(s)</rights><rights>2020 Author(s). 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A.</creatorcontrib><title>Influence of small attack angles on the transition on the wing with the subsonic leading edge at M=2</title><title>AIP Conference Proceedings</title><description>The paper is devoted to an experimental study of laminar-turbulent transition in supersonic boundary layers on swept wings. The experiments were fulfilled in the low nose supersonic wind tunnel T-325 of Khristianovich Institute of Theoretical and Applied Mechanics on the models of a swept wing with a swept angle of 72° at Mach 2 which corresponds to a subsonic leading edge. The transition location was determined using a constant temperature hot-wire anemometer. A comparison of the influence of small angles of attack on the transition position with a model with a supersonic leading edge is shown. The transition to a wing model with a subsonic leading edge occurs earlier than on a wing model with a supersonic leading edge. The angle of attack has a significant effect on the position of the transition point from the laminar to turbulent flow. The data presented in the article are among the first results for a swept wing with a subsonic leading edge.</description><subject>Angle of attack</subject><subject>Boundary layer transition</subject><subject>Computational fluid dynamics</subject><subject>Laminar flow</subject><subject>Supersonic boundary layers</subject><subject>Supersonic wind tunnels</subject><subject>Swept wings</subject><subject>Transition points</subject><subject>Turbulent boundary layer</subject><subject>Turbulent flow</subject><issn>0094-243X</issn><issn>1551-7616</issn><fulltext>true</fulltext><rsrctype>conference_proceeding</rsrctype><creationdate>2020</creationdate><recordtype>conference_proceeding</recordtype><recordid>eNotUMtOwzAQtBBIlMKBP7DEDSnFa8ePHDigikelIi4gcYvceNOmpE6JHSH-HpfmsqvZGc1oh5BrYDNgStzJGWPc8EKekAlICZlWoE7JhLEiz3guPs_JRQjbJCq0NhPiFr5uB_QV0q6mYWfbltoYbfVFrV-3GGjnadwgjb31oYlNguPlp_HrNOLmH4VhFTrfVLRF6w4MujUmK_p6zy_JWW3bgFfjnpKPp8f3-Uu2fHtezB-W2Z6DiVkupBa1ZpXUaArFkKtq5YyusTYAIjdgleROAwPB3CoH7QQgCmMBVeLFlNwcffd99z1giOW2G3qfIkuey5wLLlJHU3J7VIWqifbwUbnvm53tf0tg5aHFUpZji-IP9nZijA</recordid><startdate>20201026</startdate><enddate>20201026</enddate><creator>Semionov, N. 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A.</creatorcontrib><collection>Technology Research Database</collection><collection>Aerospace Database</collection><collection>Advanced Technologies Database with Aerospace</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext</fulltext></delivery><addata><au>Semionov, N. V.</au><au>Kosinov, A. D.</au><au>Yermolaev, Yu. G.</au><au>Kocharin, V. L.</au><au>Shipul, S. A.</au><au>Yatskikh, A. A.</au><au>Fomin, Vasily</au><format>book</format><genre>proceeding</genre><ristype>CONF</ristype><atitle>Influence of small attack angles on the transition on the wing with the subsonic leading edge at M=2</atitle><btitle>AIP Conference Proceedings</btitle><date>2020-10-26</date><risdate>2020</risdate><volume>2288</volume><issue>1</issue><issn>0094-243X</issn><eissn>1551-7616</eissn><coden>APCPCS</coden><abstract>The paper is devoted to an experimental study of laminar-turbulent transition in supersonic boundary layers on swept wings. The experiments were fulfilled in the low nose supersonic wind tunnel T-325 of Khristianovich Institute of Theoretical and Applied Mechanics on the models of a swept wing with a swept angle of 72° at Mach 2 which corresponds to a subsonic leading edge. The transition location was determined using a constant temperature hot-wire anemometer. A comparison of the influence of small angles of attack on the transition position with a model with a supersonic leading edge is shown. The transition to a wing model with a subsonic leading edge occurs earlier than on a wing model with a supersonic leading edge. The angle of attack has a significant effect on the position of the transition point from the laminar to turbulent flow. The data presented in the article are among the first results for a swept wing with a subsonic leading edge.</abstract><cop>Melville</cop><pub>American Institute of Physics</pub><doi>10.1063/5.0028295</doi><tpages>5</tpages></addata></record> |
| fulltext | fulltext |
| identifier | ISSN: 0094-243X |
| ispartof | AIP Conference Proceedings, 2020, Vol.2288 (1) |
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| language | eng |
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| source | AIP Journals Complete |
| subjects | Angle of attack Boundary layer transition Computational fluid dynamics Laminar flow Supersonic boundary layers Supersonic wind tunnels Swept wings Transition points Turbulent boundary layer Turbulent flow |
| title | Influence of small attack angles on the transition on the wing with the subsonic leading edge at M=2 |
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