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dc.contributor.advisorPlatzer, Max F.
dc.contributor.authorMarvin, Ronald E.
dc.dateSeptember 1995
dc.date.accessioned2013-08-13T22:06:52Z
dc.date.available2013-08-13T22:06:52Z
dc.date.issued1995-09
dc.identifier.urihttp://hdl.handle.net/10945/35166
dc.description.abstractIt was the objective of this investigation to study the subsonic flow over a missile forebody. To this end, the NASA Ames developed OVERFLOW, three dimensional, Navier-Stokes Code was applied and detailed results were obtained for the missile forebody. The flow conditions were set at a Mach Number of 0.3 and Reynolds Number of two million for each angle of attack at 0, 2, 6, 10, and 14 degrees. These viscous flow solutions were compared with three inviscid flow solutions, namely Slender Body Theory, von Karman's Method, and the NASA Ames Panel Code called PMARC. As expected, the OVERFLOW and PMARC solutions were in good agreement at zero and small angles of attack. As the angle of attack was increased, the OVERFLOW solution showed the development of the vortical flow separation on the leeward side of the body.en_US
dc.description.urihttp://archive.org/details/numericalinvesti1094535166
dc.format.extent117 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. Copyright protection is not available for this work in the United States.en_US
dc.titleNumerical investigation of subsonic flow over bodies of revolution and a typical missile forebodyen_US
dc.typeThesisen_US
dc.description.serviceU.S. Army (USA) authoren_US
etd.thesisdegree.nameDegree of Aeronautical Engineeren_US
etd.thesisdegree.levelProfessional Degreeen_US
etd.thesisdegree.grantorNaval Postgraduate Schoolen_US


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