Show simple item record

dc.contributor.advisorHartfield, Roy
dc.contributor.advisorBurkhalter, Johnen_US
dc.contributor.advisorJenkins, Ronen_US
dc.contributor.advisorShelton, Andrewen_US
dc.contributor.authorAhuja, Viveken_US
dc.date.accessioned2009-02-23T15:54:01Z
dc.date.available2009-02-23T15:54:01Z
dc.date.issued2008-12-15en_US
dc.identifier.urihttp://hdl.handle.net/10415/1406
dc.description.abstractA new methodology for the optimization of fuel-air mixing in a scramjet combustor using integrated Genetic Algorithms and Computational Fluid Dynamics is presented. A typical combustor design involving Mach 2 crossflow over a rearward facing step with staged normal injection is considered for study and is optimized using this method. The CFD results are validated against experimental results prior to optimization to allow for grid refinement and high accuracy of results. Quantification of typical combustor performance and design parameters is discussed and adaptation for use with CFD grids is presented. An integrated system of computers and software designed for fast computation times has been created. Correlations between variations in physical geometry and optimization of fuel-air mixing are presented.en_US
dc.language.isoen_USen_US
dc.subjectAerospace Engineeringen_US
dc.titleOptimization of Fuel-Air Mixing for a Scramjet Combustor Geometry Using CFD and a Genetic Algorithmen_US
dc.typeThesisen_US
dc.embargo.lengthNO_RESTRICTIONen_US
dc.embargo.statusNOT_EMBARGOEDen_US


Files in this item

Show simple item record