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A nozzle boundary layer model including the subsonic sublayer usable for determining boundary layer effects on plume flowfieldsA model for the boundary layer at the exit plane of a rocket nozzle was developed which, unlike most previous models, includes the subsonic sublayer. The equations for the flow near the nozzle exit plane are presented and the method by which the subsonic sublayer transitions to supersonic flow in the plume is described. The resulting model describes the entire boundary layer and can be used to provide a startline for method-of-characteristics calculations of plume flowfields. The model was incorporated into a method of characteristics computer program and comparisons of computed results to experimental data show good agreement. The data used in the comparisons were obtained in tests in which mass fluxes from a 22.2-N (5 lbf) thrust engine were measured at angles off the nozzle centerline of up to 150 deg. Additional comparisons were made with data obtained during tests of a 0.89-N (0.2 lbr) monopropellant thruster and from the OH-64 space shuttle heating tests. The agreement with the data indicates that the model can be used for calculating plume backflow properties.
Document ID
19800021927
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Cooper, B. P., Jr.
(McDonnell-Douglas Astronautics Co. Huntington Beach, CA, United States)
Date Acquired
August 10, 2013
Publication Date
July 1, 1979
Publication Information
Publication: APL JANNAF 11th Plume Technol. Meeting, Vol. 2
Subject Category
Spacecraft Propulsion And Power
Accession Number
80N30428
Funding Number(s)
CONTRACT_GRANT: NAS8-21810
CONTRACT_GRANT: NAS8-31644
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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