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Experimental determination of convective heat transfer coefficients in the separated flow region of the Space Shuttle Solid Rocket MotorA series of cold flow heat transfer tests was conducted with a 7.5-percent scale model of the Space Shuttle Rocket Motor (SRM) to measure the heat transfer coefficients in the separated flow region around the nose of the submerged nozzle. Modifications were made to an existing 7.5 percent scale model of the internal geometry of the aft end of the SRM, including the gimballed nozzle in order to accomplish the measurements. The model nozzle nose was fitted with a stainless steel shell with numerous thermocouples welded to the backside of the thin wall. A transient 'thin skin' experimental technique was used to measure the local heat transfer coefficients. The effects of Reynolds number, nozzle gimbal angle, and model location were correlated with a Stanton number versus Reynolds number correlation which may be used to determine the convective heating rates for the full scale Space Shuttle Solid Rocket Motor nozzle.
Document ID
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Whitesides, R. Harold
(Spectra Research Systems, Inc. Huntsville, AL, United States)
Majumdar, Alok K.
(Spectra Research Systems, Inc. Huntsville, AL, United States)
Jenkins, Susan L.
(SRS Technologies Huntsville, AL, United States)
Bacchus, David L.
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Date Acquired
August 14, 2013
Publication Date
January 1, 1990
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA PAPER 90-0043
Accession Number
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