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A procedure for calculation of boundary layer trip protuberances in overexpanded rocket nozzlesA procedure is described for sizing, scaling, positioning and performance loss calculation of a boundary layer trip protuberance. The theoretical results are compared with some experimental data. The application of boundary layer trips, such as secondary injection, wall angle discontinuities, circumferential grooves, and circumferential trip protuberances for reducing side loads on rocket nozzle walls is discussed.
Document ID
19740017691
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Schmucker, R. H. (National Academy of Sciences - National Research Council)
Date Acquired
September 3, 2013
Publication Date
April 2, 1973
Subject Category
Fluid Mechanics
Report/Patent Number
NASA-TM-X-64843
Report Number: NASA-TM-X-64843
Accession Number
74N25804
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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