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dc.contributor.authorCummings, Mary L.
dc.dateSeptember, 1994
dc.date.accessioned2013-04-26T19:00:04Z
dc.date.available2013-04-26T19:00:04Z
dc.date.issued1994-09
dc.identifier.urihttp://hdl.handle.net/10945/30930
dc.description.abstractA FORTRAN computer code (SKlNTEMP) has been developed to calculate transient missile/aircraft aerodynamic heating parametcrs utilizing basic flight parameters such a<; altitude, Mach number, and angle of attack. The insulated skin temperature of a vehicle surface on either the fuselage (axisymmetric body) or wing (two-dimensional body) is computed from a basic heat balance relationship throughout the enlire spectrum (subsonic, transonic, supersonic, hypersonic) of flight. This calculation method employs a simple finite diffcrenee procedure which considers radiation, forced convection, and non-reactive chemistry. Surface pressure estimates arc ba<>ed on a modified Newtonian flow model. Eckert's reference temperature method is used as the forced convection heat transfer model. SKlNTEMP predictions are compared with a limited number of test cases. SKlNTEMP was developed as a tool to enhance the conceptual design process of high speed missiles and aircraft. Recommendations are made for possible future development of SKINTEMP to further support the design process.
dc.description.urihttp://archive.org/details/acomputercodeski1094530930
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.titleA computer code (SKINTEMP) for predicting transient missile and aircraft heat transfer characteristicsen_US
dc.contributor.secondreaderNA
dc.contributor.corporateNA
dc.subject.authorNAen_US
dc.description.funderNAen_US
etd.thesisdegree.levelMastersen_US
etd.thesisdegree.grantorNaval Postgraduate Schoolen_US


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