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dc.contributor.advisorPlatzer, M.
dc.contributor.authorChadwick, William Richard
dc.date.accessioned2012-11-20T00:27:11Z
dc.date.available2012-11-20T00:27:11Z
dc.date.issued1975-06
dc.identifier.urihttp://hdl.handle.net/10945/21108
dc.descriptionApproved for public release; distribution unlimiteden_US
dc.description.abstractSeveral problems are treated which arise in the study of generalized airforces in unsteady supersonic cascades having subsonic axial velocity. The finite cascade of oscillating wedges is first solved numerically. When the thickness is very small, the general nonlinear solution agrees with results based on the linear theory of characteristics, while for the single wedge oscillating near shock detachment it agrees closely with Carrier's exact solution. There is some indication that thickness effects are reduced by cascading. Next, the finite cascade of oscillating flat plates is solved analytically, to the third power of oscillation frequency. The generalized surface pressure is shown to agree with exact numerical results for moderate blade index, but diverges in the far field of the cascade. For comparison with the finite cascade, there is presented finally an elementary periodic solution for the infinite cascade. A simple relationship between the two basic cascade models is developed. The investigation is presently restricted to flow regions upstream of Mach wave reflections in the blade passages.en_US
dc.description.urihttp://archive.org/details/unsteadysuperson00chad
dc.language.isoen_US
dc.subject.lcshAeronauticsen_US
dc.titleUnsteady supersonic cascade theory including nonlinear thickness effectsen_US
dc.typeThesisen_US
dc.subject.authorUnsteady supersonic cascade theoryen_US
dc.subject.authorNonlinear thickness effectsen_US
dc.description.serviceResearch Associate, Naval Surface Weapons Centeren_US
etd.thesisdegree.namePh.D.en_US
etd.thesisdegree.levelDoctoralen_US
etd.thesisdegree.grantorNaval Postgraduate Schoolen_US


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