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dc.contributor.advisorLigrani, Phillip M.
dc.contributor.authorWigle, James Michael
dc.date.accessioned2013-01-23T22:09:12Z
dc.date.available2013-01-23T22:09:12Z
dc.date.issued1991-12
dc.identifier.urihttp://hdl.handle.net/10945/27076
dc.description.abstractExperimental results are presented which describe the development and structure of flow downstream of one row and downstream of two staggered rows of film-cooling holes with compound angle orientations. Results presented include distributions of iso-energetic Stanton number ratios, and adiabatic film-cooling effectiveness deduced from Stanton numbers using superposition. Also presented are plots showing the streamwise development of injectant distributions and streamwise development of mean velocity distributions. Spanwise averaged values of the adiabatic film-cooling effectiveness are highest for blowing ratio m=0.5 and decrease as blowing ratio increases for x/d less than 20. At farther downstream positions, spanwise averaged effectiveness values increase with blowing ratio, except for data obtained downstream of two rows of holes with a blowing ratio of 3.0 and data obtained downstream of two rows of holes with a blowing ratio of 3.0 and data obtained downstream of one row of holes with a blowing ratio of 4.0, where severe lift-off of injectant occurs. Spanwise averaged iso-energetic Stanton number ratios range between 1.0 and 1.4 and show little variation as x/d increases for each value of blowing ratio, however for each x/d, values increase with increasing blowing ratio.en_US
dc.description.urihttp://archive.org/details/heattransferdiab1094527076
dc.format.extent244 p.;28 cm.en_US
dc.language.isoen_US
dc.publisherMonterey, California. Naval Postgraduate Schoolen_US
dc.titleHeat transfer, adiabatic effectiveness and injectant distribution downstream of single and double rows of film-cooling holes with compound angles.en_US
dc.typeThesisen_US
dc.contributor.corporateNaval Postgraduate School
dc.contributor.schoolNaval Postgraduate School
dc.contributor.departmentMechanical Engineering
dc.subject.authorcompound angle injectionen_US
dc.subject.authorfilm-coolingen_US
dc.subject.authorturbulent boundary layeren_US
dc.description.serviceLieutenant Commander, United States 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
dc.description.distributionstatementApproved for public release; distribution is unlimited.


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