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dc.contributor.advisorGopinath, Ashok
dc.contributor.authorSavur, Mehmet Koray
dc.date.accessioned2012-03-14T17:38:03Z
dc.date.available2012-03-14T17:38:03Z
dc.date.issued2002-12
dc.identifier.urihttp://hdl.handle.net/10945/3338
dc.descriptionApproved for public release; distribution in unlimited.en_US
dc.description.abstractA numerical study was conducted to predict the combined convective and radiative heat transfer rates on the walls of a small aspect ratio cylinder representative of the scaled model of arocket engine combustion chamber. A high-temperature, high-pressure environment was simulated in the cylinder, with gas velocities at low subsonic levels typical of the conditions leading to the entrance of the nozzle section of a rocket engine. The composition of the gases in the cylinder was determined from the TEP program for the burning of rocket fuel at typical values of the O/Fratio. The thrust of the study was to determine the radiative contribution to the heat transfer rate from the hot participating chamber gases to the cooler wall. The calculations were carried out using the commercial CFD package CFDACE, and were first benchmarked against known results in the literature for the simpler case of gray chamber walls and a gray participating medium. Thenon-gray computations were subsequently carried out using gas absorption coefficient values obtained from the exponential wide band model with the help of the fire-modeling program, RADCAL.The effect of different chamber wall temperatures and gas compositions were examined. The main findings of the study are that the radiative contributions at the high gas temperatures being considered are comparable to the convective values, and strongly spectral in nature. In addition these radiative fluxes were found to be least sensitive to the wall temperature and chamber pressure in the range considered. Furthermore, this radiative contribution reaches a maximum at aunique optimal optical thickness of the gas that lies within the extremes of the optically thin and thick limiting cases.en_US
dc.description.urihttp://archive.org/details/anumericalstudyo109453338
dc.format.extentxiv, 83 p. : ill. (some col.) ;en_US
dc.publisherMonterey, California. Naval Postgraduate Schoolen_US
dc.rightsCopyright is reserved by the copyright owner.en_US
dc.subject.lcshHeaten_US
dc.subject.lcshRadiation and absorptionen_US
dc.subject.lcshRocket enginesen_US
dc.subject.lcshCombustionen_US
dc.titleA numerical study of combined convective and radiative heat transfer in a rocket engine combustion chamberen_US
dc.typeThesisen_US
dc.contributor.departmentMechanical
dc.subject.authorRadiative Heat Transferen_US
dc.subject.authorRocket Engineen_US
dc.subject.authorCombustion Chamberen_US
dc.subject.authorRADCALen_US
dc.subject.authorTEPen_US
dc.subject.authorCFD-ACEen_US
dc.subject.authornon-gray gasen_US
dc.subject.authorspectral transmissivityen_US
dc.subject.authorabsorption coefficienten_US
dc.description.serviceLieutenant Junior Grade, Turkish Navyen_US
etd.thesisdegree.nameM.S. in Mechanical Engineeringen_US
etd.thesisdegree.levelMastersen_US
etd.thesisdegree.disciplineMechanical Engineeringen_US
etd.thesisdegree.grantorNaval Postgraduate Schoolen_US


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