Advanced Mixing Control in Supersonic Airstream with a Wall-Mounted Cavity
The acoustic wave impinging effect on the initial condition of the supersonic mixing layer growth is investigated. The flow at the 2D nozzle exit was shown with the axes whose origin was set on the center of the injector exit. Near the injector exit, an expansion fan followed by a recompression wave...
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| Veröffentlicht in: | Journal of propulsion and power 1999-03, Vol.15 (2), p.358-360 |
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| container_issue | 2 |
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| container_title | Journal of propulsion and power |
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| creator | Sato, N Imamura, A Shiba, S Takahashi, S Tsue, M Kono, M |
| description | The acoustic wave impinging effect on the initial condition of the supersonic mixing layer growth is investigated. The flow at the 2D nozzle exit was shown with the axes whose origin was set on the center of the injector exit. Near the injector exit, an expansion fan followed by a recompression wave is observed. From the observation, the oscillation was caused by the same oscillation of the mixing layer in the synchronized image along with the instantaneous one. When the fluctuations of the beam intensity passing through the mixing layer were detected downstream, nearly the same fundamental frequency with the acoustic disturbance was obtained. |
| doi_str_mv | 10.2514/2.5433 |
| format | Article |
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The flow at the 2D nozzle exit was shown with the axes whose origin was set on the center of the injector exit. Near the injector exit, an expansion fan followed by a recompression wave is observed. From the observation, the oscillation was caused by the same oscillation of the mixing layer in the synchronized image along with the instantaneous one. When the fluctuations of the beam intensity passing through the mixing layer were detected downstream, nearly the same fundamental frequency with the acoustic disturbance was obtained.</description><identifier>ISSN: 0748-4658</identifier><identifier>EISSN: 1533-3876</identifier><identifier>DOI: 10.2514/2.5433</identifier><language>eng</language><publisher>Reston: American Institute of Aeronautics and Astronautics</publisher><subject>Acoustic waves ; Cavitation ; Exhaust systems (engine) ; Flow control ; Flow interactions ; Nozzles ; Oscillations ; Wall flow</subject><ispartof>Journal of propulsion and power, 1999-03, Vol.15 (2), p.358-360</ispartof><rights>Copyright American Institute of Aeronautics and Astronautics Mar/Apr 1999</rights><lds50>peer_reviewed</lds50><woscitedreferencessubscribed>false</woscitedreferencessubscribed><citedby>FETCH-LOGICAL-a404t-2c4089ac0bcc0760227411240d8b41edf1ff6733dcedb2ea67d88d62ace7c523</citedby><cites>FETCH-LOGICAL-a404t-2c4089ac0bcc0760227411240d8b41edf1ff6733dcedb2ea67d88d62ace7c523</cites></display><links><openurl>$$Topenurl_article</openurl><openurlfulltext>$$Topenurlfull_article</openurlfulltext><thumbnail>$$Tsyndetics_thumb_exl</thumbnail><link.rule.ids>314,780,784,27924,27925</link.rule.ids></links><search><creatorcontrib>Sato, N</creatorcontrib><creatorcontrib>Imamura, A</creatorcontrib><creatorcontrib>Shiba, S</creatorcontrib><creatorcontrib>Takahashi, S</creatorcontrib><creatorcontrib>Tsue, M</creatorcontrib><creatorcontrib>Kono, M</creatorcontrib><title>Advanced Mixing Control in Supersonic Airstream with a Wall-Mounted Cavity</title><title>Journal of propulsion and power</title><description>The acoustic wave impinging effect on the initial condition of the supersonic mixing layer growth is investigated. The flow at the 2D nozzle exit was shown with the axes whose origin was set on the center of the injector exit. Near the injector exit, an expansion fan followed by a recompression wave is observed. From the observation, the oscillation was caused by the same oscillation of the mixing layer in the synchronized image along with the instantaneous one. When the fluctuations of the beam intensity passing through the mixing layer were detected downstream, nearly the same fundamental frequency with the acoustic disturbance was obtained.</description><subject>Acoustic waves</subject><subject>Cavitation</subject><subject>Exhaust systems (engine)</subject><subject>Flow control</subject><subject>Flow interactions</subject><subject>Nozzles</subject><subject>Oscillations</subject><subject>Wall flow</subject><issn>0748-4658</issn><issn>1533-3876</issn><fulltext>true</fulltext><rsrctype>article</rsrctype><creationdate>1999</creationdate><recordtype>article</recordtype><recordid>eNqNkV1LwzAUhoMoOKf-hoKg3lTznfRyFD_Z8MKBlyFLU83o2pqkc_v3dkwYqIhX5-I85-G8vACcIniFGaLX-IpRQvbAADFCUiIF3wcDKKhMKWfyEByFMIcQccnFADyOiqWujS2SiVu5-jXJmzr6pkpcnTx3rfWhqZ1JRs6H6K1eJB8uviU6edFVlU6aro79aa6XLq6PwUGpq2BPvuYQTG9vpvl9On66e8hH41RTSGOKDYUy0wbOjIGCQ4wFRQhTWMgZRbYoUVlyQUjRPzXDVnNRSFlwrI0VhmEyBBdbbeub986GqBYuGFtVurZNF5SgnCAG-_BDcP4niXmGCYTkPyCSlKEePPsGzpvO131ahQnCmWCEZzud8U0I3paq9W6h_VohqDYVKaw2Fe102mm9U_2gLn-jtlvVFqUqu6qKdhXJJxaQmoA</recordid><startdate>19990301</startdate><enddate>19990301</enddate><creator>Sato, N</creator><creator>Imamura, A</creator><creator>Shiba, S</creator><creator>Takahashi, S</creator><creator>Tsue, M</creator><creator>Kono, M</creator><general>American Institute of Aeronautics and Astronautics</general><scope>AAYXX</scope><scope>CITATION</scope><scope>7TB</scope><scope>8FD</scope><scope>FR3</scope><scope>H8D</scope><scope>L7M</scope><scope>KR7</scope><scope>7TC</scope></search><sort><creationdate>19990301</creationdate><title>Advanced Mixing Control in Supersonic Airstream with a Wall-Mounted Cavity</title><author>Sato, N ; Imamura, A ; Shiba, S ; Takahashi, S ; Tsue, M ; Kono, M</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-LOGICAL-a404t-2c4089ac0bcc0760227411240d8b41edf1ff6733dcedb2ea67d88d62ace7c523</frbrgroupid><rsrctype>articles</rsrctype><prefilter>articles</prefilter><language>eng</language><creationdate>1999</creationdate><topic>Acoustic waves</topic><topic>Cavitation</topic><topic>Exhaust systems (engine)</topic><topic>Flow control</topic><topic>Flow interactions</topic><topic>Nozzles</topic><topic>Oscillations</topic><topic>Wall flow</topic><toplevel>peer_reviewed</toplevel><toplevel>online_resources</toplevel><creatorcontrib>Sato, N</creatorcontrib><creatorcontrib>Imamura, A</creatorcontrib><creatorcontrib>Shiba, S</creatorcontrib><creatorcontrib>Takahashi, S</creatorcontrib><creatorcontrib>Tsue, M</creatorcontrib><creatorcontrib>Kono, M</creatorcontrib><collection>CrossRef</collection><collection>Mechanical & Transportation Engineering Abstracts</collection><collection>Technology Research Database</collection><collection>Engineering Research Database</collection><collection>Aerospace Database</collection><collection>Advanced Technologies Database with Aerospace</collection><collection>Civil Engineering Abstracts</collection><collection>Mechanical Engineering Abstracts</collection><jtitle>Journal of propulsion and power</jtitle></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext</fulltext></delivery><addata><au>Sato, N</au><au>Imamura, A</au><au>Shiba, S</au><au>Takahashi, S</au><au>Tsue, M</au><au>Kono, M</au><format>journal</format><genre>article</genre><ristype>JOUR</ristype><atitle>Advanced Mixing Control in Supersonic Airstream with a Wall-Mounted Cavity</atitle><jtitle>Journal of propulsion and power</jtitle><date>1999-03-01</date><risdate>1999</risdate><volume>15</volume><issue>2</issue><spage>358</spage><epage>360</epage><pages>358-360</pages><issn>0748-4658</issn><eissn>1533-3876</eissn><abstract>The acoustic wave impinging effect on the initial condition of the supersonic mixing layer growth is investigated. 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| fulltext | fulltext |
| identifier | ISSN: 0748-4658 |
| ispartof | Journal of propulsion and power, 1999-03, Vol.15 (2), p.358-360 |
| issn | 0748-4658 1533-3876 |
| language | eng |
| recordid | cdi_proquest_journals_2312975369 |
| source | Alma/SFX Local Collection |
| subjects | Acoustic waves Cavitation Exhaust systems (engine) Flow control Flow interactions Nozzles Oscillations Wall flow |
| title | Advanced Mixing Control in Supersonic Airstream with a Wall-Mounted Cavity |
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