NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Investigation of extendable nozzle conceptsPreliminary research and technology were performed toward the development of a transpiration cooled inflatable nozzle extension. The J-2 engine of the Saturn-Apollo launch vehicle was selected as a design application test bed to provide realistic operational parameters and a possible hot firing demonstration. The nozzle extension attached at the 27.5 to 1 area ratio of the basic J-2 nozzle exit and extended to an area ratio of 48 to 1. The final nozzle extension design as evolved during this effort utilized conically woven stainless steel airmat as the major construction material. Model and full scale nozzle extensions were fabricated and tested although an actual J-2 hot firing demonstration was not possible due to the lack of a proper altitude test opportunity.
Document ID
19730011573
Document Type
Contractor Report (CR)
Authors
Scott, C. N. (Goodyear Aerospace Corp. Akron, OH, United States)
Nordlie, R. W. (Goodyear Aerospace Corp. Akron, OH, United States)
Sowa, W. W. (Goodyear Aerospace Corp. Akron, OH, United States)
Date Acquired
September 2, 2013
Publication Date
November 1, 1972
Subject Category
FLUID MECHANICS
Report/Patent Number
NASA-CR-124165
GER-15240
Funding Number(s)
CONTRACT_GRANT: NAS8-21476
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

Available Downloads

NameType 19730011573.pdf STI