Combustion Efficiencies and Flameout Limits Computed for a Hypersonic Vehicle During Ascent
Computations were performed to understand propulsion tradeoffs that occur when a hypersonic vehicle travels along an ascent trajectory. Operability limits are plotted that define allowable flight corridors on an altitude versus flight Mach number performance map. Two operability limits are set by re...
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Veröffentlicht in: | Journal of propulsion and power 2018-05, Vol.34 (3), p.624-635 |
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creator | Mbagwu, Chukwuka C Driscoll, James F Dalle, Derek J Torrez, Sean M |
description | Computations were performed to understand propulsion tradeoffs that occur when a hypersonic vehicle travels along an ascent trajectory. Operability limits are plotted that define allowable flight corridors on an altitude versus flight Mach number performance map. Two operability limits are set by requirements that combustion efficiency exceeds 0.90 and that flameout be avoided. Ambient gas pressure decreases during ascent, which for a fixed waverider inlet (compressor) design slows finite rate chemistry in the combustor. However, this can be offset by increases in flight Mach number and gas temperature in the combustor. New aspects of the work are that operability limits are computed for a waverider trimmed at each altitude. The University of Michigan–U.S. Air Force Research Laboratory scramjet in vehicle waverider model includes finite rate chemistry, three-dimensional mixing, ram–scram transition, and an empirical value of the flameout Damköhler number. A reduced-order modeling approach is justified (instead of computational fluid dynamics results) because all vehicle forces are computed over 1800 times to generate multidimensional performance maps. Trajectories were optimized to achieve highest combustion efficiency and avoid flameout limits. |
doi_str_mv | 10.2514/1.B36479 |
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Operability limits are plotted that define allowable flight corridors on an altitude versus flight Mach number performance map. Two operability limits are set by requirements that combustion efficiency exceeds 0.90 and that flameout be avoided. Ambient gas pressure decreases during ascent, which for a fixed waverider inlet (compressor) design slows finite rate chemistry in the combustor. However, this can be offset by increases in flight Mach number and gas temperature in the combustor. New aspects of the work are that operability limits are computed for a waverider trimmed at each altitude. The University of Michigan–U.S. Air Force Research Laboratory scramjet in vehicle waverider model includes finite rate chemistry, three-dimensional mixing, ram–scram transition, and an empirical value of the flameout Damköhler number. A reduced-order modeling approach is justified (instead of computational fluid dynamics results) because all vehicle forces are computed over 1800 times to generate multidimensional performance maps. Trajectories were optimized to achieve highest combustion efficiency and avoid flameout limits.</description><identifier>ISSN: 0748-4658</identifier><identifier>EISSN: 1533-3876</identifier><identifier>DOI: 10.2514/1.B36479</identifier><language>eng</language><publisher>Reston: American Institute of Aeronautics and Astronautics</publisher><subject>Aerodynamics ; Altitude ; Ascent trajectories ; Combustion chambers ; Combustion efficiency ; Computational fluid dynamics ; Corridors ; Flameout ; Flight corridors ; Gas pressure ; Gas temperature ; Hypersonic vehicles ; Mach number ; Organic chemistry ; Reduced order models ; Supersonic combustion ramjet engines ; Three dimensional models ; Trajectory optimization</subject><ispartof>Journal of propulsion and power, 2018-05, Vol.34 (3), p.624-635</ispartof><rights>Copyright © 2017 by Chukwuka C. Mbagwu. 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 ISSN (print) or (online) to initiate your request. See also AIAA Rights and Permissions .</rights><rights>Copyright © 2017 by Chukwuka C. Mbagwu. 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 ISSN 0748-4658 (print) or 1533-3876 (online) to initiate your request. 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Operability limits are plotted that define allowable flight corridors on an altitude versus flight Mach number performance map. Two operability limits are set by requirements that combustion efficiency exceeds 0.90 and that flameout be avoided. Ambient gas pressure decreases during ascent, which for a fixed waverider inlet (compressor) design slows finite rate chemistry in the combustor. However, this can be offset by increases in flight Mach number and gas temperature in the combustor. New aspects of the work are that operability limits are computed for a waverider trimmed at each altitude. The University of Michigan–U.S. Air Force Research Laboratory scramjet in vehicle waverider model includes finite rate chemistry, three-dimensional mixing, ram–scram transition, and an empirical value of the flameout Damköhler number. A reduced-order modeling approach is justified (instead of computational fluid dynamics results) because all vehicle forces are computed over 1800 times to generate multidimensional performance maps. Trajectories were optimized to achieve highest combustion efficiency and avoid flameout limits.</description><subject>Aerodynamics</subject><subject>Altitude</subject><subject>Ascent trajectories</subject><subject>Combustion chambers</subject><subject>Combustion efficiency</subject><subject>Computational fluid dynamics</subject><subject>Corridors</subject><subject>Flameout</subject><subject>Flight corridors</subject><subject>Gas pressure</subject><subject>Gas temperature</subject><subject>Hypersonic vehicles</subject><subject>Mach number</subject><subject>Organic chemistry</subject><subject>Reduced order models</subject><subject>Supersonic combustion ramjet engines</subject><subject>Three dimensional models</subject><subject>Trajectory optimization</subject><issn>0748-4658</issn><issn>1533-3876</issn><fulltext>true</fulltext><rsrctype>article</rsrctype><creationdate>2018</creationdate><recordtype>article</recordtype><recordid>eNp90MtKAzEUgOEgCtYq-AgBEdyMJs1lkmWtrRUKbtSNiyGTi6Z0JmOSWfTtnTKCC8HF4Ww-_gMHgEuMbmcM0zt8e084LeURmGBGSEFEyY_BBJVUFJQzcQrOUtoihLng5QS8L0JT9yn70MKlc1572w6ToGoNXO1UY0Of4cY3Pic42K7P1kAXIlRwve9sTKH1Gr7ZT693Fj700bcfcJ60bfM5OHFql-zFz56C19XyZbEuNs-PT4v5plAUk1yI0iBOrDHcGOxkLaljCDNnbC0kdszoWpSUKGOkQgprbSnjgipKhHS1lGQKrsZuF8NXb1OutqGP7XCymlFJmBhy5b8Kc8wlQeLQuhmVjiGlaF3VRd-ouK8wqg4PrnA1Pnig1yNVXqnf2B_3DahoeEs</recordid><startdate>20180501</startdate><enddate>20180501</enddate><creator>Mbagwu, Chukwuka C</creator><creator>Driscoll, James F</creator><creator>Dalle, Derek J</creator><creator>Torrez, Sean 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></search><sort><creationdate>20180501</creationdate><title>Combustion Efficiencies and Flameout Limits Computed for a Hypersonic Vehicle During Ascent</title><author>Mbagwu, Chukwuka C ; Driscoll, James F ; Dalle, Derek J ; Torrez, Sean M</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-LOGICAL-a413t-87d063edd6dd1f9b94f5015fdeb891f5dcb8743add9a0a1cce45684a4389fb993</frbrgroupid><rsrctype>articles</rsrctype><prefilter>articles</prefilter><language>eng</language><creationdate>2018</creationdate><topic>Aerodynamics</topic><topic>Altitude</topic><topic>Ascent trajectories</topic><topic>Combustion chambers</topic><topic>Combustion efficiency</topic><topic>Computational fluid dynamics</topic><topic>Corridors</topic><topic>Flameout</topic><topic>Flight corridors</topic><topic>Gas pressure</topic><topic>Gas temperature</topic><topic>Hypersonic vehicles</topic><topic>Mach number</topic><topic>Organic chemistry</topic><topic>Reduced order models</topic><topic>Supersonic combustion ramjet engines</topic><topic>Three dimensional models</topic><topic>Trajectory optimization</topic><toplevel>peer_reviewed</toplevel><toplevel>online_resources</toplevel><creatorcontrib>Mbagwu, Chukwuka C</creatorcontrib><creatorcontrib>Driscoll, James F</creatorcontrib><creatorcontrib>Dalle, Derek J</creatorcontrib><creatorcontrib>Torrez, Sean 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><jtitle>Journal of propulsion and power</jtitle></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext</fulltext></delivery><addata><au>Mbagwu, Chukwuka C</au><au>Driscoll, James F</au><au>Dalle, Derek J</au><au>Torrez, Sean M</au><format>journal</format><genre>article</genre><ristype>JOUR</ristype><atitle>Combustion Efficiencies and Flameout Limits Computed for a Hypersonic Vehicle During Ascent</atitle><jtitle>Journal of propulsion and power</jtitle><date>2018-05-01</date><risdate>2018</risdate><volume>34</volume><issue>3</issue><spage>624</spage><epage>635</epage><pages>624-635</pages><issn>0748-4658</issn><eissn>1533-3876</eissn><abstract>Computations were performed to understand propulsion tradeoffs that occur when a hypersonic vehicle travels along an ascent trajectory. Operability limits are plotted that define allowable flight corridors on an altitude versus flight Mach number performance map. Two operability limits are set by requirements that combustion efficiency exceeds 0.90 and that flameout be avoided. Ambient gas pressure decreases during ascent, which for a fixed waverider inlet (compressor) design slows finite rate chemistry in the combustor. However, this can be offset by increases in flight Mach number and gas temperature in the combustor. New aspects of the work are that operability limits are computed for a waverider trimmed at each altitude. The University of Michigan–U.S. Air Force Research Laboratory scramjet in vehicle waverider model includes finite rate chemistry, three-dimensional mixing, ram–scram transition, and an empirical value of the flameout Damköhler number. A reduced-order modeling approach is justified (instead of computational fluid dynamics results) because all vehicle forces are computed over 1800 times to generate multidimensional performance maps. Trajectories were optimized to achieve highest combustion efficiency and avoid flameout limits.</abstract><cop>Reston</cop><pub>American Institute of Aeronautics and Astronautics</pub><doi>10.2514/1.B36479</doi><tpages>12</tpages><oa>free_for_read</oa></addata></record> |
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subjects | Aerodynamics Altitude Ascent trajectories Combustion chambers Combustion efficiency Computational fluid dynamics Corridors Flameout Flight corridors Gas pressure Gas temperature Hypersonic vehicles Mach number Organic chemistry Reduced order models Supersonic combustion ramjet engines Three dimensional models Trajectory optimization |
title | Combustion Efficiencies and Flameout Limits Computed for a Hypersonic Vehicle During Ascent |
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