Numerical Study of Hypersonic Boundary-Layer Receptivity with Freestream Hotspot Perturbations
This paper presents a numerical-simulation study of transient flow over a blunt compression cone under the effect of freestream hotspot perturbations. This study is motivated by concurrent wind-tunnel laser-spot experiments carried out at Purdue University. The flow conditions used in the simulation...
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| Veröffentlicht in: | AIAA journal 2014-12, Vol.52 (12), p.2652-2672 |
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| creator | Huang, Yuet Zhong, Xiaolin |
| description | This paper presents a numerical-simulation study of transient flow over a blunt compression cone under the effect of freestream hotspot perturbations. This study is motivated by concurrent wind-tunnel laser-spot experiments carried out at Purdue University. The flow conditions used in the simulation are based on the experimental conditions. The simulation is performed using a high-order shock-fitting finite-difference scheme. The simulation results show that the hotspot is able to excite second-mode instability, where the instability growth is found to be dominant in the boundary layer. The receptivity mechanism is investigated by comparing the simulated results with linear-stability theory. Fast acoustic waves generated by hotspot–shock interaction excite the boundary-layer disturbances. Also, the synchronization of mode F and mode S leads to the dominance of boundary-layer disturbances by the growing second mode. |
| doi_str_mv | 10.2514/1.J052657 |
| format | Article |
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This study is motivated by concurrent wind-tunnel laser-spot experiments carried out at Purdue University. The flow conditions used in the simulation are based on the experimental conditions. The simulation is performed using a high-order shock-fitting finite-difference scheme. The simulation results show that the hotspot is able to excite second-mode instability, where the instability growth is found to be dominant in the boundary layer. The receptivity mechanism is investigated by comparing the simulated results with linear-stability theory. Fast acoustic waves generated by hotspot–shock interaction excite the boundary-layer disturbances. Also, the synchronization of mode F and mode S leads to the dominance of boundary-layer disturbances by the growing second mode.</description><identifier>ISSN: 0001-1452</identifier><identifier>EISSN: 1533-385X</identifier><identifier>DOI: 10.2514/1.J052657</identifier><identifier>CODEN: AIAJAH</identifier><language>eng</language><publisher>Reston, VA: American Institute of Aeronautics and Astronautics</publisher><subject>Acoustic waves ; Aerodynamics ; Aerospace engineering ; Boundaries ; Boundary layer ; Boundary layers ; Compressible flows; shock and detonation phenomena ; Computer simulation ; Disturbances ; Exact sciences and technology ; Excitation ; Finite difference method ; Fluid dynamics ; Fundamental areas of phenomenology (including applications) ; Hot spots ; Hydrodynamic stability ; Instability ; Perturbation ; Perturbation methods ; Physics ; Receptivity ; Simulation ; Supersonic and hypersonic flows ; Synchronism ; Unsteady flow ; Wind tunnels</subject><ispartof>AIAA journal, 2014-12, Vol.52 (12), p.2652-2672</ispartof><rights>Copyright © 2014 by Yuet Huang and Xiaolin Zhong. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission. Copies of this paper may be made for personal or internal use, on condition that the copier pay the $10.00 per-copy fee to the Copyright Clearance Center, Inc., 222 Rosewood Drive, Danvers, MA 01923; include the code and $10.00 in correspondence with the CCC.</rights><rights>2015 INIST-CNRS</rights><rights>Copyright © 2014 by Yuet Huang and Xiaolin Zhong. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission. Copies of this paper may be made for personal or internal use, on condition that the copier pay the $10.00 per-copy fee to the Copyright Clearance Center, Inc., 222 Rosewood Drive, Danvers, MA 01923; include the code 1533-385X/14 and $10.00 in correspondence with the CCC.</rights><lds50>peer_reviewed</lds50><woscitedreferencessubscribed>false</woscitedreferencessubscribed><citedby>FETCH-LOGICAL-a379t-12a54c1ac7f4027c5fac62667a50ebc347e7ea1032ab1043753c6ba1da4ce0213</citedby><cites>FETCH-LOGICAL-a379t-12a54c1ac7f4027c5fac62667a50ebc347e7ea1032ab1043753c6ba1da4ce0213</cites></display><links><openurl>$$Topenurl_article</openurl><openurlfulltext>$$Topenurlfull_article</openurlfulltext><thumbnail>$$Tsyndetics_thumb_exl</thumbnail><link.rule.ids>314,776,780,27901,27902</link.rule.ids><backlink>$$Uhttp://pascal-francis.inist.fr/vibad/index.php?action=getRecordDetail&idt=29121242$$DView record in Pascal Francis$$Hfree_for_read</backlink></links><search><creatorcontrib>Huang, Yuet</creatorcontrib><creatorcontrib>Zhong, Xiaolin</creatorcontrib><title>Numerical Study of Hypersonic Boundary-Layer Receptivity with Freestream Hotspot Perturbations</title><title>AIAA journal</title><description>This paper presents a numerical-simulation study of transient flow over a blunt compression cone under the effect of freestream hotspot perturbations. This study is motivated by concurrent wind-tunnel laser-spot experiments carried out at Purdue University. The flow conditions used in the simulation are based on the experimental conditions. The simulation is performed using a high-order shock-fitting finite-difference scheme. The simulation results show that the hotspot is able to excite second-mode instability, where the instability growth is found to be dominant in the boundary layer. The receptivity mechanism is investigated by comparing the simulated results with linear-stability theory. Fast acoustic waves generated by hotspot–shock interaction excite the boundary-layer disturbances. Also, the synchronization of mode F and mode S leads to the dominance of boundary-layer disturbances by the growing second mode.</description><subject>Acoustic waves</subject><subject>Aerodynamics</subject><subject>Aerospace engineering</subject><subject>Boundaries</subject><subject>Boundary layer</subject><subject>Boundary layers</subject><subject>Compressible flows; shock and detonation phenomena</subject><subject>Computer simulation</subject><subject>Disturbances</subject><subject>Exact sciences and technology</subject><subject>Excitation</subject><subject>Finite difference method</subject><subject>Fluid dynamics</subject><subject>Fundamental areas of phenomenology (including applications)</subject><subject>Hot spots</subject><subject>Hydrodynamic stability</subject><subject>Instability</subject><subject>Perturbation</subject><subject>Perturbation methods</subject><subject>Physics</subject><subject>Receptivity</subject><subject>Simulation</subject><subject>Supersonic and hypersonic flows</subject><subject>Synchronism</subject><subject>Unsteady flow</subject><subject>Wind tunnels</subject><issn>0001-1452</issn><issn>1533-385X</issn><fulltext>true</fulltext><rsrctype>article</rsrctype><creationdate>2014</creationdate><recordtype>article</recordtype><recordid>eNp9kVuLE0EQhRtZwRh98B80LIr7MLGrL9PJoxvMRgkqXsAnh0qnBjsk07PdPcr8e1sSFlHYp6Lgq1OHcxh7BmImDehXMHsnjKyNfcAmYJSq1Nx8u2ATIQRUoI18xB6ntC-btHOYsO_vhyNF7_DAP-dhN_LQ8vXYU0yh845fh6HbYRyrDY4U-Sdy1Gf_0-eR__L5B19FopQj4ZGvQ059yPwjxTzELWYfuvSEPWzxkOjpeU7Z19WbL8t1tflw83b5elOhsotcgUSjHaCzrRbSOtOiq2VdWzSCtk5pS5YQhJK4BaGVNcrVW4QdakdCgpqylyfdPobboVhqjj45OhywozCkBuoSjrBFs6CX_6D7MMSuuGukXoDSoO6noJZzVYsSd6GuTpSLIaVIbdNHfyx5NSCaP3000Jz7KOzzsyKmEncbsXM-3R3IBUiQWhbuxYlDj_jX1_8EfwP11JSt</recordid><startdate>20141201</startdate><enddate>20141201</enddate><creator>Huang, Yuet</creator><creator>Zhong, Xiaolin</creator><general>American Institute of Aeronautics and Astronautics</general><scope>IQODW</scope><scope>AAYXX</scope><scope>CITATION</scope><scope>7TB</scope><scope>8FD</scope><scope>FR3</scope><scope>H8D</scope><scope>L7M</scope></search><sort><creationdate>20141201</creationdate><title>Numerical Study of Hypersonic Boundary-Layer Receptivity with Freestream Hotspot Perturbations</title><author>Huang, Yuet ; Zhong, Xiaolin</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-LOGICAL-a379t-12a54c1ac7f4027c5fac62667a50ebc347e7ea1032ab1043753c6ba1da4ce0213</frbrgroupid><rsrctype>articles</rsrctype><prefilter>articles</prefilter><language>eng</language><creationdate>2014</creationdate><topic>Acoustic waves</topic><topic>Aerodynamics</topic><topic>Aerospace engineering</topic><topic>Boundaries</topic><topic>Boundary layer</topic><topic>Boundary layers</topic><topic>Compressible flows; shock and detonation phenomena</topic><topic>Computer simulation</topic><topic>Disturbances</topic><topic>Exact sciences and technology</topic><topic>Excitation</topic><topic>Finite difference method</topic><topic>Fluid dynamics</topic><topic>Fundamental areas of phenomenology (including applications)</topic><topic>Hot spots</topic><topic>Hydrodynamic stability</topic><topic>Instability</topic><topic>Perturbation</topic><topic>Perturbation methods</topic><topic>Physics</topic><topic>Receptivity</topic><topic>Simulation</topic><topic>Supersonic and hypersonic flows</topic><topic>Synchronism</topic><topic>Unsteady flow</topic><topic>Wind tunnels</topic><toplevel>peer_reviewed</toplevel><toplevel>online_resources</toplevel><creatorcontrib>Huang, Yuet</creatorcontrib><creatorcontrib>Zhong, Xiaolin</creatorcontrib><collection>Pascal-Francis</collection><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>Huang, Yuet</au><au>Zhong, Xiaolin</au><format>journal</format><genre>article</genre><ristype>JOUR</ristype><atitle>Numerical Study of Hypersonic Boundary-Layer Receptivity with Freestream Hotspot Perturbations</atitle><jtitle>AIAA journal</jtitle><date>2014-12-01</date><risdate>2014</risdate><volume>52</volume><issue>12</issue><spage>2652</spage><epage>2672</epage><pages>2652-2672</pages><issn>0001-1452</issn><eissn>1533-385X</eissn><coden>AIAJAH</coden><abstract>This paper presents a numerical-simulation study of transient flow over a blunt compression cone under the effect of freestream hotspot perturbations. This study is motivated by concurrent wind-tunnel laser-spot experiments carried out at Purdue University. The flow conditions used in the simulation are based on the experimental conditions. The simulation is performed using a high-order shock-fitting finite-difference scheme. The simulation results show that the hotspot is able to excite second-mode instability, where the instability growth is found to be dominant in the boundary layer. The receptivity mechanism is investigated by comparing the simulated results with linear-stability theory. Fast acoustic waves generated by hotspot–shock interaction excite the boundary-layer disturbances. Also, the synchronization of mode F and mode S leads to the dominance of boundary-layer disturbances by the growing second mode.</abstract><cop>Reston, VA</cop><pub>American Institute of Aeronautics and Astronautics</pub><doi>10.2514/1.J052657</doi><tpages>21</tpages></addata></record> |
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| subjects | Acoustic waves Aerodynamics Aerospace engineering Boundaries Boundary layer Boundary layers Compressible flows shock and detonation phenomena Computer simulation Disturbances Exact sciences and technology Excitation Finite difference method Fluid dynamics Fundamental areas of phenomenology (including applications) Hot spots Hydrodynamic stability Instability Perturbation Perturbation methods Physics Receptivity Simulation Supersonic and hypersonic flows Synchronism Unsteady flow Wind tunnels |
| title | Numerical Study of Hypersonic Boundary-Layer Receptivity with Freestream Hotspot Perturbations |
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