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dc.contributor.advisorNewberry, Conrad F.
dc.contributor.advisorBowles, Jeffrey V.
dc.contributor.authorPrice, David R.
dc.dateJune 1993
dc.date.accessioned2014-03-26T23:23:27Z
dc.date.available2014-03-26T23:23:27Z
dc.date.issued1993-06
dc.identifier.urihttp://hdl.handle.net/10945/39832
dc.descriptionApproved for public release; distribution is unlimited.en_US
dc.description.abstractAn aircraft configuration for a deck launched intercept mission was investigated. The mission requirements for the carrier-launched and recovered aircraft included Mach 6 cruise out to a 1000 nautical mile combat radius and 20 minutes of combat followed by return to the carrier. A conical-flow waverider served as the starting point for the aircraft configuration. A hydrocarbon scramjet was integrated with the waverider body. The aft end of the waverider was faired to decrease the base area thereby reducing the transonic base drag. A numerical optimization was then completed to maximize the product of L/D (lift to drag ratio) and I sub sp (specific impulse). Variables for the optimization included the cone shock angle (used to derive the conical flow waverider) and the geometry of both the waverider body and the integrated propulsion system. The vehicle was constrained to a minimum volume of 3240 cubic feet, a maximum span of 60 feet and a fixed length of 60 feet. The integrated propulsion system was constrained to produce a minimum contraction ratio of 12.0 and assurance that the cowl shock was within an acceptable distance of the inlet shoulder of the combustor. The optimum configuration met or exceeded all constraints. L/D comparisons were made between the integrated configuration (i.e., the subject of this study), pure Mach 6 optimized waveriders and historical trends.en_US
dc.description.urihttp://archive.org/details/optimizationndpe1094539832
dc.format.extent72 p.en_US
dc.language.isoen_US
dc.publisherMonterey, California. Naval Postgraduate Schoolen_US
dc.rightsThis publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. As such, it is in the public domain, and under the provisions of Title 17, United States Code, Section 105, may not be copyrighted.en_US
dc.titleOptimization and performance analysis of a supersonic conical-flow waverider for a deck-launched intercept missionen_US
dc.typeThesisen_US
dc.contributor.corporateNaval Postgraduate School (U.S.)
dc.contributor.departmentDepartment of Aeronautics and Astronautics
dc.subject.authorWaveridersen_US
dc.subject.authorHypersonicsen_US
dc.subject.authorAircraft designen_US
dc.description.serviceLieutenant, United States Navyen_US
etd.thesisdegree.nameM.S. in Astronautical Engineeringen_US
etd.thesisdegree.levelMastersen_US
etd.thesisdegree.disciplineAstronautical Engineeringen_US
etd.thesisdegree.grantorNaval Postgraduate Schoolen_US


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