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Acoustical and Flowfield Characterization of a Scaled Tabletop RocketAn analysis of the acoustical and flowfield environment for the scaled 1-pound-force (lbf) thrust tabletop motor was performed. This tabletop motor from NASA Stennis Space Center Is composed of Plexiglas burning In gaseous oxygen with a graphite insert for the nozzle portion. The nozzle has a throat diameter of 0.2 inch and an exit diameter of 0.38 Inch. With a chamber pressure at 55 pounds per square Inch absolute (psia), a normal shock is formed immediately downstream of the nozzle exit plane as the combustion products exhaust into the ambient at atmospheric pressure. The jet characterization Is based on computational fluid dynamics (CFD) in conjunction with Kirchhoff surface integral formulation and compared with correlations developed for measured rocket noise and a pressure fluctuation scaling (PFS) method. Predictions and comparisons are made for the overall sound pressure levels (OASPL's) and spectral dependence of sound pressure level (SPL). The overall objective of this effort is to develop methods for scaling the acoustic and flowfield environment of rockets with a wide range of thrust (1 lbf to 1 million lbf).
Document ID
20010090338
Acquisition Source
Kennedy Space Center
Document Type
Technical Memorandum (TM)
Authors
Kandula, Max (DYNACS Engineering Co., Inc. Cocoa Beach, FL United States)
Margasahayam, Ravi (DYNACS Engineering Co., Inc. Cocoa Beach, FL United States)
Norton, Michael (University of Western Australia Crawley Australia)
Caimi, Raoul (NASA Kennedy Space Center Cocoa Beach, FL United States)
Steinrock, T.
Venegas, Augusto
Date Acquired
September 7, 2013
Publication Date
July 1, 2001
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
NAS 1.15:210262
NASA/TM-2001-210262
Funding Number(s)
CONTRACT_GRANT: NAS10-98001
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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