Control of Pressure Oscillations Induced by Supersonic Cavity Flow
A control method is developed to suppress pressure oscillations induced by supersonic cavity flow using high-speed upstream injection. The injection is generated with a large blowing coefficient through a channel, which guides the airflow blowing off in the leading edge of the cavity. Wind tunnel ex...
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| Veröffentlicht in: | AIAA journal 2020-05, Vol.58 (5), p.2070-2077 |
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| container_end_page | 2077 |
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| container_title | AIAA journal |
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| creator | Xiansheng, Wang Dangguo, Yang Jun, Liu Fangqi, Zhou |
| description | A control method is developed to suppress pressure oscillations induced by supersonic cavity flow using high-speed upstream injection. The injection is generated with a large blowing coefficient through a channel, which guides the airflow blowing off in the leading edge of the cavity. Wind tunnel experiments are performed to validate the method with Mach 1.8 and 2.0 flows over a length-to-depth 6 cavity. Six dynamic pressure transducers are used to characterize the cavity oscillation. A remarkable suppression of pressure fluctuation is realized in the controlled cavity flow. The overall sound pressure level can be reduced by larger than 10 dB in both configurations. The most remarkable reduction in pressure fluctuation occurs near the cavity trailing edge, wherein flow-induced oscillation is strongest. Almost no cavity tones are observed near the cavity trailing edge under control. Further, the control method is proven effective and stable over time. The feedback loop is interrupted in the controlled cavity flow with a weak impact of shear vortices on the cavity aft wall. The control method may be a practical and potential candidate for use in engineering applications because it does not need additional gas supply in the control system. |
| doi_str_mv | 10.2514/1.J059014 |
| format | Article |
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The injection is generated with a large blowing coefficient through a channel, which guides the airflow blowing off in the leading edge of the cavity. Wind tunnel experiments are performed to validate the method with Mach 1.8 and 2.0 flows over a length-to-depth 6 cavity. Six dynamic pressure transducers are used to characterize the cavity oscillation. A remarkable suppression of pressure fluctuation is realized in the controlled cavity flow. The overall sound pressure level can be reduced by larger than 10 dB in both configurations. The most remarkable reduction in pressure fluctuation occurs near the cavity trailing edge, wherein flow-induced oscillation is strongest. Almost no cavity tones are observed near the cavity trailing edge under control. Further, the control method is proven effective and stable over time. The feedback loop is interrupted in the controlled cavity flow with a weak impact of shear vortices on the cavity aft wall. The control method may be a practical and potential candidate for use in engineering applications because it does not need additional gas supply in the control system.</description><identifier>ISSN: 0001-1452</identifier><identifier>EISSN: 1533-385X</identifier><identifier>DOI: 10.2514/1.J059014</identifier><language>eng</language><publisher>Virginia: American Institute of Aeronautics and Astronautics</publisher><subject>Aerodynamics ; Air flow ; Blowing rate ; Cavity flow ; Control theory ; Dynamic pressure ; Feedback loops ; Fluid dynamics ; Fluid flow ; Pressure oscillations ; Sound pressure ; Trailing edges ; Transducers ; Wind tunnel testing ; Wind tunnels</subject><ispartof>AIAA journal, 2020-05, Vol.58 (5), p.2070-2077</ispartof><rights>Copyright © 2020 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved. All requests for copying and permission to reprint should be submitted to CCC at ; employ the eISSN to initiate your request. See also AIAA Rights and Permissions .</rights><rights>Copyright © 2020 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved. All requests for copying and permission to reprint should be submitted to CCC at www.copyright.com; employ the eISSN 1533-385X to initiate your request. 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The injection is generated with a large blowing coefficient through a channel, which guides the airflow blowing off in the leading edge of the cavity. Wind tunnel experiments are performed to validate the method with Mach 1.8 and 2.0 flows over a length-to-depth 6 cavity. Six dynamic pressure transducers are used to characterize the cavity oscillation. A remarkable suppression of pressure fluctuation is realized in the controlled cavity flow. The overall sound pressure level can be reduced by larger than 10 dB in both configurations. The most remarkable reduction in pressure fluctuation occurs near the cavity trailing edge, wherein flow-induced oscillation is strongest. Almost no cavity tones are observed near the cavity trailing edge under control. Further, the control method is proven effective and stable over time. The feedback loop is interrupted in the controlled cavity flow with a weak impact of shear vortices on the cavity aft wall. The control method may be a practical and potential candidate for use in engineering applications because it does not need additional gas supply in the control system.</description><subject>Aerodynamics</subject><subject>Air flow</subject><subject>Blowing rate</subject><subject>Cavity flow</subject><subject>Control theory</subject><subject>Dynamic pressure</subject><subject>Feedback loops</subject><subject>Fluid dynamics</subject><subject>Fluid flow</subject><subject>Pressure oscillations</subject><subject>Sound pressure</subject><subject>Trailing edges</subject><subject>Transducers</subject><subject>Wind tunnel testing</subject><subject>Wind tunnels</subject><issn>0001-1452</issn><issn>1533-385X</issn><fulltext>true</fulltext><rsrctype>article</rsrctype><creationdate>2020</creationdate><recordtype>article</recordtype><recordid>eNpl0F1LwzAUBuAgCtbphf8gIAhedJ58LcmlFqeTwQQVvAtZk0JHbWbSKvv3dnTghVeHAw_v4bwIXRKYUkH4LZk-g9BA-BHKiGAsZ0p8HKMMAEhOuKCn6CylzbBRqUiG7ovQdjE0OFT4JfqU-ujxKpV109iuDm3Ci9b1pXd4vcOv_dbHFNq6xIX9rrsdnjfh5xydVLZJ_uIwJ-h9_vBWPOXL1eOiuFvmlirV5W7GPYVKWsE4URq0toJKX9pSa5AOhJJUrZnnVM64dsoxqe0MNAjvCKscm6CrMXcbw1fvU2c2oY_tcNJQpjnfv0sHdTOqMoaUoq_MNtafNu4MAbOvyBBzqGiw16O1tbV_af_hL525Ym4</recordid><startdate>20200501</startdate><enddate>20200501</enddate><creator>Xiansheng, Wang</creator><creator>Dangguo, Yang</creator><creator>Jun, Liu</creator><creator>Fangqi, Zhou</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></search><sort><creationdate>20200501</creationdate><title>Control of Pressure Oscillations Induced by Supersonic Cavity Flow</title><author>Xiansheng, Wang ; Dangguo, Yang ; Jun, Liu ; Fangqi, Zhou</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-LOGICAL-a288t-d64e20f7a534189099a527ecac9907d058728b3e427649d8d379a60905ed13fd3</frbrgroupid><rsrctype>articles</rsrctype><prefilter>articles</prefilter><language>eng</language><creationdate>2020</creationdate><topic>Aerodynamics</topic><topic>Air flow</topic><topic>Blowing rate</topic><topic>Cavity flow</topic><topic>Control theory</topic><topic>Dynamic pressure</topic><topic>Feedback loops</topic><topic>Fluid dynamics</topic><topic>Fluid flow</topic><topic>Pressure oscillations</topic><topic>Sound pressure</topic><topic>Trailing edges</topic><topic>Transducers</topic><topic>Wind tunnel testing</topic><topic>Wind tunnels</topic><toplevel>peer_reviewed</toplevel><toplevel>online_resources</toplevel><creatorcontrib>Xiansheng, Wang</creatorcontrib><creatorcontrib>Dangguo, Yang</creatorcontrib><creatorcontrib>Jun, Liu</creatorcontrib><creatorcontrib>Fangqi, Zhou</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><jtitle>AIAA journal</jtitle></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext</fulltext></delivery><addata><au>Xiansheng, Wang</au><au>Dangguo, Yang</au><au>Jun, Liu</au><au>Fangqi, Zhou</au><format>journal</format><genre>article</genre><ristype>JOUR</ristype><atitle>Control of Pressure Oscillations Induced by Supersonic Cavity Flow</atitle><jtitle>AIAA journal</jtitle><date>2020-05-01</date><risdate>2020</risdate><volume>58</volume><issue>5</issue><spage>2070</spage><epage>2077</epage><pages>2070-2077</pages><issn>0001-1452</issn><eissn>1533-385X</eissn><abstract>A control method is developed to suppress pressure oscillations induced by supersonic cavity flow using high-speed upstream injection. The injection is generated with a large blowing coefficient through a channel, which guides the airflow blowing off in the leading edge of the cavity. Wind tunnel experiments are performed to validate the method with Mach 1.8 and 2.0 flows over a length-to-depth 6 cavity. Six dynamic pressure transducers are used to characterize the cavity oscillation. A remarkable suppression of pressure fluctuation is realized in the controlled cavity flow. The overall sound pressure level can be reduced by larger than 10 dB in both configurations. The most remarkable reduction in pressure fluctuation occurs near the cavity trailing edge, wherein flow-induced oscillation is strongest. Almost no cavity tones are observed near the cavity trailing edge under control. Further, the control method is proven effective and stable over time. The feedback loop is interrupted in the controlled cavity flow with a weak impact of shear vortices on the cavity aft wall. The control method may be a practical and potential candidate for use in engineering applications because it does not need additional gas supply in the control system.</abstract><cop>Virginia</cop><pub>American Institute of Aeronautics and Astronautics</pub><doi>10.2514/1.J059014</doi><tpages>8</tpages></addata></record> |
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| source | Alma/SFX Local Collection |
| subjects | Aerodynamics Air flow Blowing rate Cavity flow Control theory Dynamic pressure Feedback loops Fluid dynamics Fluid flow Pressure oscillations Sound pressure Trailing edges Transducers Wind tunnel testing Wind tunnels |
| title | Control of Pressure Oscillations Induced by Supersonic Cavity Flow |
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