Concave Bump for Impinging-Shock Control in Supersonic Flows
In the present study, a novel concave bump for impinging-shock control in two-dimensional supersonic flows is investigated. An analytical method for preliminary bump design based on a generalized shape of a shock-canceling bump has been developed and verified numerically. An extensive proof-of-conce...
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| Veröffentlicht in: | AIAA journal 2022-05, Vol.60 (5), p.2749-2766 |
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| creator | Schülein, Erich Schnepf, Christian Weiss, Sebastian |
| description | In the present study, a novel concave bump for impinging-shock control in two-dimensional supersonic flows is investigated. An analytical method for preliminary bump design based on a generalized shape of a shock-canceling bump has been developed and verified numerically. An extensive proof-of-concept study was performed at a freestream Mach number ranging from 2.5 to 5.0 for shock-generator angles varying from 6 to 12 degrees. It could be demonstrated that a concave bump designed for a given flow-deflection angle is capable of significantly reducing the size of the separation bubble as well as the total pressure losses throughout the Mach number range investigated. The achievable gains depend on the Mach number, the flow-deflection angle, and the relative impingement position of the incident shock front on the bump. The highest values of separation-length reduction (up to 100%), momentum thickness reduction (up to 31%), and pressure recovery factor increase (up to 33%) were obtained at the optimum shock impingement position for the largest deflection angle studied. The concave bump is less effective, and in some cases even disadvantageous, when the incident shock wave does not optimally strike the bump crest. |
| doi_str_mv | 10.2514/1.J060799 |
| format | Article |
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An analytical method for preliminary bump design based on a generalized shape of a shock-canceling bump has been developed and verified numerically. An extensive proof-of-concept study was performed at a freestream Mach number ranging from 2.5 to 5.0 for shock-generator angles varying from 6 to 12 degrees. It could be demonstrated that a concave bump designed for a given flow-deflection angle is capable of significantly reducing the size of the separation bubble as well as the total pressure losses throughout the Mach number range investigated. The achievable gains depend on the Mach number, the flow-deflection angle, and the relative impingement position of the incident shock front on the bump. The highest values of separation-length reduction (up to 100%), momentum thickness reduction (up to 31%), and pressure recovery factor increase (up to 33%) were obtained at the optimum shock impingement position for the largest deflection angle studied. The concave bump is less effective, and in some cases even disadvantageous, when the incident shock wave does not optimally strike the bump crest.</description><identifier>ISSN: 0001-1452</identifier><identifier>EISSN: 1533-385X</identifier><identifier>DOI: 10.2514/1.J060799</identifier><language>eng</language><publisher>Virginia: American Institute of Aeronautics and Astronautics</publisher><subject>Deflection ; High speed ; Impingement ; Mach number ; Optimization ; Pressure loss ; Pressure recovery ; Reduction ; Reynolds number ; Separation ; Supersonic flow ; Two dimensional analysis ; Two dimensional flow</subject><ispartof>AIAA journal, 2022-05, Vol.60 (5), p.2749-2766</ispartof><rights>Copyright © 2021 by Erich Schülein, Christian Schnepf, and Sebastian Weiss. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission. 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 © 2021 by Erich Schülein, Christian Schnepf, and Sebastian Weiss. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission. 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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An analytical method for preliminary bump design based on a generalized shape of a shock-canceling bump has been developed and verified numerically. An extensive proof-of-concept study was performed at a freestream Mach number ranging from 2.5 to 5.0 for shock-generator angles varying from 6 to 12 degrees. It could be demonstrated that a concave bump designed for a given flow-deflection angle is capable of significantly reducing the size of the separation bubble as well as the total pressure losses throughout the Mach number range investigated. The achievable gains depend on the Mach number, the flow-deflection angle, and the relative impingement position of the incident shock front on the bump. The highest values of separation-length reduction (up to 100%), momentum thickness reduction (up to 31%), and pressure recovery factor increase (up to 33%) were obtained at the optimum shock impingement position for the largest deflection angle studied. The concave bump is less effective, and in some cases even disadvantageous, when the incident shock wave does not optimally strike the bump crest.</description><subject>Deflection</subject><subject>High speed</subject><subject>Impingement</subject><subject>Mach number</subject><subject>Optimization</subject><subject>Pressure loss</subject><subject>Pressure recovery</subject><subject>Reduction</subject><subject>Reynolds number</subject><subject>Separation</subject><subject>Supersonic flow</subject><subject>Two dimensional analysis</subject><subject>Two dimensional flow</subject><issn>0001-1452</issn><issn>1533-385X</issn><fulltext>true</fulltext><rsrctype>article</rsrctype><creationdate>2022</creationdate><recordtype>article</recordtype><recordid>eNpl0EtLAzEQAOAgCtbqwX8QEAQPqZmk2Qd40cVqpeChCt5CXqtbt5s16Sr-eyMteBAGhhm-mYFB6BTohAmYXsLkgWY0L8s9NALBOeGFeNlHI0opEJgKdoiOYlyliuUFjNBV5TujPh2-GdY9rn3A83XfdK8pyPLNm3ecwCb4FjcdXg69C9F3jcGz1n_FY3RQqza6k10eo-fZ7VN1TxaPd_PqekEUK_mGsNIa7bTNbKaoNQy0ri3PtEsNqm1NFYPclSLn2lBlmTZTDjwrE2a5FYKP0dl2bx_8x-DiRq78ELp0UrJMFCyNFpDUxVaZ4GMMrpZ9aNYqfEug8vc5EuTuOcmeb61qlPrb9h_-ANAAYfw</recordid><startdate>202205</startdate><enddate>202205</enddate><creator>Schülein, Erich</creator><creator>Schnepf, Christian</creator><creator>Weiss, Sebastian</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><orcidid>https://orcid.org/0000-0002-1125-8504</orcidid></search><sort><creationdate>202205</creationdate><title>Concave Bump for Impinging-Shock Control in Supersonic Flows</title><author>Schülein, Erich ; Schnepf, Christian ; Weiss, Sebastian</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-LOGICAL-a293t-29dcbebd6d6a0dc21bbfd36be6d60bdf0a217e9573bc0ad2bc431369a0d27d553</frbrgroupid><rsrctype>articles</rsrctype><prefilter>articles</prefilter><language>eng</language><creationdate>2022</creationdate><topic>Deflection</topic><topic>High speed</topic><topic>Impingement</topic><topic>Mach number</topic><topic>Optimization</topic><topic>Pressure loss</topic><topic>Pressure recovery</topic><topic>Reduction</topic><topic>Reynolds number</topic><topic>Separation</topic><topic>Supersonic flow</topic><topic>Two dimensional analysis</topic><topic>Two dimensional flow</topic><toplevel>peer_reviewed</toplevel><toplevel>online_resources</toplevel><creatorcontrib>Schülein, Erich</creatorcontrib><creatorcontrib>Schnepf, Christian</creatorcontrib><creatorcontrib>Weiss, Sebastian</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>Schülein, Erich</au><au>Schnepf, Christian</au><au>Weiss, Sebastian</au><format>journal</format><genre>article</genre><ristype>JOUR</ristype><atitle>Concave Bump for Impinging-Shock Control in Supersonic Flows</atitle><jtitle>AIAA journal</jtitle><date>2022-05</date><risdate>2022</risdate><volume>60</volume><issue>5</issue><spage>2749</spage><epage>2766</epage><pages>2749-2766</pages><issn>0001-1452</issn><eissn>1533-385X</eissn><abstract>In the present study, a novel concave bump for impinging-shock control in two-dimensional supersonic flows is investigated. An analytical method for preliminary bump design based on a generalized shape of a shock-canceling bump has been developed and verified numerically. An extensive proof-of-concept study was performed at a freestream Mach number ranging from 2.5 to 5.0 for shock-generator angles varying from 6 to 12 degrees. It could be demonstrated that a concave bump designed for a given flow-deflection angle is capable of significantly reducing the size of the separation bubble as well as the total pressure losses throughout the Mach number range investigated. The achievable gains depend on the Mach number, the flow-deflection angle, and the relative impingement position of the incident shock front on the bump. The highest values of separation-length reduction (up to 100%), momentum thickness reduction (up to 31%), and pressure recovery factor increase (up to 33%) were obtained at the optimum shock impingement position for the largest deflection angle studied. The concave bump is less effective, and in some cases even disadvantageous, when the incident shock wave does not optimally strike the bump crest.</abstract><cop>Virginia</cop><pub>American Institute of Aeronautics and Astronautics</pub><doi>10.2514/1.J060799</doi><tpages>18</tpages><orcidid>https://orcid.org/0000-0002-1125-8504</orcidid><oa>free_for_read</oa></addata></record> |
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| source | Alma/SFX Local Collection |
| subjects | Deflection High speed Impingement Mach number Optimization Pressure loss Pressure recovery Reduction Reynolds number Separation Supersonic flow Two dimensional analysis Two dimensional flow |
| title | Concave Bump for Impinging-Shock Control in Supersonic Flows |
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