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A new concept of a variable-Mach-number perforated wall nozzle for providing a supersonic external stream in rocket-propulsion testing.Perforated wall nozzle providing variable Mach number supersonic flow for external stream simulation in rocket propulsion tests
Document ID
19680042689
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Hendershot, K. G.
Sheeran, W. J.
Date Acquired
August 4, 2013
Publication Date
March 1, 1968
Publication Information
Publisher: AMERICAN INST. OF AERONAUTICS AND ASTRONAUTICS.
Subject Category
Facilities, Research, And Support
Report/Patent Number
AIAA PAPER 68-238
Report Number: AIAA PAPER 68-238
Meeting Information
Meeting: FLIGHT TEST, SIMULATION AND SUPPORT CONFERENCE
Location: LOS ANGELES, CA
Start Date: March 25, 1968
End Date: March 27, 1968
Sponsors: AMERICAN INST. OF AERONAUTICS AND ASTRONAUTICS
Accession Number
68A23661
Funding Number(s)
CONTRACT_GRANT: NAS8-20027
Distribution Limits
Public
Copyright
Other

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