Publication:
The Effect of Stagnation Temperature and Molecular Weight Variation on Gaseous Injection Into A Supersonic Stream.

dc.contributor.advisorCollins, Daniel J.
dc.contributor.authorChrans, Larry "J"
dc.contributor.corporateNaval Postgraduate School (U.S.)
dc.date1968-09
dc.date.accessioned2014-03-27T21:10:22Z
dc.date.available2014-03-27T21:10:22Z
dc.date.issued1968-09
dc.description.abstractThe purpose of the study was to investigate the effect of injectant stagnation temperature and molecular weight variation on the flow field generated from secondary injection of a gas normal to a supersonic stream. Experiments were conducted at a primary stream Mach number of 2.80 in a supersonic wind tunnel. Experimental data have been correlated with various theories, showing both agreement and disagreement. Data presented include penetration of secondary jet into primary flow and shock shape as correlated with the second order blast wave theory.en_US
dc.description.distributionstatementApproved for public release; distribution is unlimited.
dc.description.serviceLieutenant, United States Navyen_US
dc.description.urihttp://archive.org/details/theeffectofstagn1094540047
dc.format.extent77 p.en_US
dc.identifier.urihttps://hdl.handle.net/10945/40047
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.titleThe Effect of Stagnation Temperature and Molecular Weight Variation on Gaseous Injection Into A Supersonic Stream.en_US
dc.typeThesisen_US
dspace.entity.typePublication
etd.thesisdegree.disciplineAeronautical Engineeringen_US
etd.thesisdegree.grantorNaval Postgraduate Schoolen_US
etd.thesisdegree.levelProfessional Degreeen_US
etd.thesisdegree.nameDegree of Aeronautical Engineeren_US
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