Trajectory Analysis of Fuel Injection into Supersonic Cross Flow Based on Schlieren Method
Trajectory analysis of fuel injection into supersonic cross flow is studied in this paper. A directly-connected wind tunnel is constructed to provide stable supersonic freestream. Based on the test rig, the schlieren system is established to reveal the fuel injection process visually. Subsequently,...
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| Veröffentlicht in: | Chinese journal of aeronautics 2012-02, Vol.25 (1), p.42-50 |
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| creator | YANG, Hui LI, Feng SUN, Baigang |
| description | Trajectory analysis of fuel injection into supersonic cross flow is studied in this paper. A directly-connected wind tunnel is constructed to provide stable supersonic freestream. Based on the test rig, the schlieren system is established to reveal the fuel injection process visually. Subsequently, the method of quantitative schlieren is adopted to obtain data of both fuel/air interface and bow shock with the aid of Photoshop and Origin. Finally, the mechanism based on two influential factors of fuel injection angle and fuel injection driven pressure, is researched by vector analysis. A dimensionless model is deduced and analyzed. The curve fitting result is achieved. The relationship between the data and the two influential factors is established. The results provide not only the quantitative characteristics of the fuel injection in supersonic cross flow but also the valuable reference for the future computational simulation. |
| doi_str_mv | 10.1016/S1000-9361(11)60360-9 |
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A directly-connected wind tunnel is constructed to provide stable supersonic freestream. Based on the test rig, the schlieren system is established to reveal the fuel injection process visually. Subsequently, the method of quantitative schlieren is adopted to obtain data of both fuel/air interface and bow shock with the aid of Photoshop and Origin. Finally, the mechanism based on two influential factors of fuel injection angle and fuel injection driven pressure, is researched by vector analysis. A dimensionless model is deduced and analyzed. The curve fitting result is achieved. The relationship between the data and the two influential factors is established. The results provide not only the quantitative characteristics of the fuel injection in supersonic cross flow but also the valuable reference for the future computational simulation.</description><identifier>ISSN: 1000-9361</identifier><identifier>DOI: 10.1016/S1000-9361(11)60360-9</identifier><language>eng</language><publisher>Elsevier Ltd</publisher><subject>characteristic velocity ; Cross flow ; Curve fitting ; Fuel injection ; injection angle ; injection driven pressure ; Mathematical models ; Photoshop ; schlieren ; Supersonic aircraft ; supersonic flow ; Trajectory analysis ; Vector analysis ; Wind tunnels ; 喷油角度 ; 影响因素 ; 燃油喷射过程 ; 纹影法 ; 计算机模拟 ; 超音速 ; 轨迹分析</subject><ispartof>Chinese journal of aeronautics, 2012-02, Vol.25 (1), p.42-50</ispartof><rights>2012 Chinese Journal of Aeronautics</rights><lds50>peer_reviewed</lds50><oa>free_for_read</oa><woscitedreferencessubscribed>false</woscitedreferencessubscribed><citedby>FETCH-LOGICAL-c415t-36175640820524090bd2c8809f8cdecd9c090ac8ac81e7a981c4a14f8baaff1d3</citedby><cites>FETCH-LOGICAL-c415t-36175640820524090bd2c8809f8cdecd9c090ac8ac81e7a981c4a14f8baaff1d3</cites></display><links><openurl>$$Topenurl_article</openurl><openurlfulltext>$$Topenurlfull_article</openurlfulltext><thumbnail>$$Uhttp://image.cqvip.com/vip1000/qk/83889X/83889X.jpg</thumbnail><linktohtml>$$Uhttps://dx.doi.org/10.1016/S1000-9361(11)60360-9$$EHTML$$P50$$Gelsevier$$Hfree_for_read</linktohtml><link.rule.ids>314,780,784,3548,27922,27923,45993</link.rule.ids></links><search><creatorcontrib>YANG, Hui</creatorcontrib><creatorcontrib>LI, Feng</creatorcontrib><creatorcontrib>SUN, Baigang</creatorcontrib><title>Trajectory Analysis of Fuel Injection into Supersonic Cross Flow Based on Schlieren Method</title><title>Chinese journal of aeronautics</title><addtitle>Chinese Journal of Aeronautics</addtitle><description>Trajectory analysis of fuel injection into supersonic cross flow is studied in this paper. A directly-connected wind tunnel is constructed to provide stable supersonic freestream. Based on the test rig, the schlieren system is established to reveal the fuel injection process visually. Subsequently, the method of quantitative schlieren is adopted to obtain data of both fuel/air interface and bow shock with the aid of Photoshop and Origin. Finally, the mechanism based on two influential factors of fuel injection angle and fuel injection driven pressure, is researched by vector analysis. A dimensionless model is deduced and analyzed. The curve fitting result is achieved. The relationship between the data and the two influential factors is established. The results provide not only the quantitative characteristics of the fuel injection in supersonic cross flow but also the valuable reference for the future computational simulation.</description><subject>characteristic velocity</subject><subject>Cross flow</subject><subject>Curve fitting</subject><subject>Fuel injection</subject><subject>injection angle</subject><subject>injection driven pressure</subject><subject>Mathematical models</subject><subject>Photoshop</subject><subject>schlieren</subject><subject>Supersonic aircraft</subject><subject>supersonic flow</subject><subject>Trajectory analysis</subject><subject>Vector analysis</subject><subject>Wind tunnels</subject><subject>喷油角度</subject><subject>影响因素</subject><subject>燃油喷射过程</subject><subject>纹影法</subject><subject>计算机模拟</subject><subject>超音速</subject><subject>轨迹分析</subject><issn>1000-9361</issn><fulltext>true</fulltext><rsrctype>article</rsrctype><creationdate>2012</creationdate><recordtype>article</recordtype><recordid>eNqFkEtPAjEQgHvQRER_gkm94WG1s-89GSSiJBgP4MVLU7qzULK00O5q-Pd2gXA1adLM9Os8PkLugD0Cg_RpBoyxoIhSGAA8pCxKfXRBeuf0Fbl2bs1YVGTAeuR7bsUaZWPsng61qPdOOWoqOm6xphPdPSmjqdKNobN2i9YZrSQdWeMcHdfml74IhyX1zEyuaoUWNf3AZmXKG3JZidrh7enuk6_x63z0Hkw_3yaj4TSQMSRN4GfKkjRmeciSMGYFW5ShzHNWVLksUZaF9Dkhc38AM1HkIGMBcZUvhKgqKKM-GRzrbq3ZtegavlFOYl0LjaZ13Hsp0iRnwDyaHFHZzW-x4lurNsLuPdRxKT_4450oDsAP_nzUJ8_Hf-j3-PFLcicVaomlst4QL436t8L9qfPK6OVO6eW5dQwhRGkWRX8AgYSu</recordid><startdate>20120201</startdate><enddate>20120201</enddate><creator>YANG, Hui</creator><creator>LI, Feng</creator><creator>SUN, Baigang</creator><general>Elsevier Ltd</general><scope>2RA</scope><scope>92L</scope><scope>CQIGP</scope><scope>W92</scope><scope>~WA</scope><scope>6I.</scope><scope>AAFTH</scope><scope>AAYXX</scope><scope>CITATION</scope><scope>7SU</scope><scope>7TB</scope><scope>8FD</scope><scope>C1K</scope><scope>FR3</scope><scope>H8D</scope><scope>L7M</scope></search><sort><creationdate>20120201</creationdate><title>Trajectory Analysis of Fuel Injection into Supersonic Cross Flow Based on Schlieren Method</title><author>YANG, Hui ; LI, Feng ; SUN, Baigang</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-LOGICAL-c415t-36175640820524090bd2c8809f8cdecd9c090ac8ac81e7a981c4a14f8baaff1d3</frbrgroupid><rsrctype>articles</rsrctype><prefilter>articles</prefilter><language>eng</language><creationdate>2012</creationdate><topic>characteristic velocity</topic><topic>Cross flow</topic><topic>Curve fitting</topic><topic>Fuel injection</topic><topic>injection angle</topic><topic>injection driven pressure</topic><topic>Mathematical models</topic><topic>Photoshop</topic><topic>schlieren</topic><topic>Supersonic aircraft</topic><topic>supersonic flow</topic><topic>Trajectory analysis</topic><topic>Vector analysis</topic><topic>Wind tunnels</topic><topic>喷油角度</topic><topic>影响因素</topic><topic>燃油喷射过程</topic><topic>纹影法</topic><topic>计算机模拟</topic><topic>超音速</topic><topic>轨迹分析</topic><toplevel>peer_reviewed</toplevel><toplevel>online_resources</toplevel><creatorcontrib>YANG, Hui</creatorcontrib><creatorcontrib>LI, Feng</creatorcontrib><creatorcontrib>SUN, Baigang</creatorcontrib><collection>中文科技期刊数据库</collection><collection>中文科技期刊数据库-CALIS站点</collection><collection>中文科技期刊数据库-7.0平台</collection><collection>中文科技期刊数据库-工程技术</collection><collection>中文科技期刊数据库- 镜像站点</collection><collection>ScienceDirect Open Access Titles</collection><collection>Elsevier:ScienceDirect:Open Access</collection><collection>CrossRef</collection><collection>Environmental Engineering Abstracts</collection><collection>Mechanical & Transportation Engineering Abstracts</collection><collection>Technology Research Database</collection><collection>Environmental Sciences and Pollution Management</collection><collection>Engineering Research Database</collection><collection>Aerospace Database</collection><collection>Advanced Technologies Database with Aerospace</collection><jtitle>Chinese journal of aeronautics</jtitle></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext</fulltext></delivery><addata><au>YANG, Hui</au><au>LI, Feng</au><au>SUN, Baigang</au><format>journal</format><genre>article</genre><ristype>JOUR</ristype><atitle>Trajectory Analysis of Fuel Injection into Supersonic Cross Flow Based on Schlieren Method</atitle><jtitle>Chinese journal of aeronautics</jtitle><addtitle>Chinese Journal of Aeronautics</addtitle><date>2012-02-01</date><risdate>2012</risdate><volume>25</volume><issue>1</issue><spage>42</spage><epage>50</epage><pages>42-50</pages><issn>1000-9361</issn><abstract>Trajectory analysis of fuel injection into supersonic cross flow is studied in this paper. A directly-connected wind tunnel is constructed to provide stable supersonic freestream. Based on the test rig, the schlieren system is established to reveal the fuel injection process visually. Subsequently, the method of quantitative schlieren is adopted to obtain data of both fuel/air interface and bow shock with the aid of Photoshop and Origin. Finally, the mechanism based on two influential factors of fuel injection angle and fuel injection driven pressure, is researched by vector analysis. A dimensionless model is deduced and analyzed. The curve fitting result is achieved. The relationship between the data and the two influential factors is established. The results provide not only the quantitative characteristics of the fuel injection in supersonic cross flow but also the valuable reference for the future computational simulation.</abstract><pub>Elsevier Ltd</pub><doi>10.1016/S1000-9361(11)60360-9</doi><tpages>9</tpages><oa>free_for_read</oa></addata></record> |
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| source | Elektronische Zeitschriftenbibliothek - Frei zugängliche E-Journals; ScienceDirect Journals (5 years ago - present) |
| subjects | characteristic velocity Cross flow Curve fitting Fuel injection injection angle injection driven pressure Mathematical models Photoshop schlieren Supersonic aircraft supersonic flow Trajectory analysis Vector analysis Wind tunnels 喷油角度 影响因素 燃油喷射过程 纹影法 计算机模拟 超音速 轨迹分析 |
| title | Trajectory Analysis of Fuel Injection into Supersonic Cross Flow Based on Schlieren Method |
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