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Flow characterization in the NASA Ames 16-inch Shock TunnelFlow characteristics of NASA's 16-Inch Shock Tunnel are determined for purposes of providing hypersonic propulsion simulation capability. The key tunnel operating parameters are the incident shock speed and reservoir pressure and enthalpy. Flow characteristics of concern are the nozzle exit pressure, temperature, Mach number, Reynolds number, chemical composition, and flow uniformity. Surface mounted gages (for pressure and heat transfer) and nonintrusive optical flow diagnostics (emission and absorption spectroscopy and holographic interferometry) are used to verify tunnel conditions. Experimental measurements are used to validate computational analysis for predicting facility performance, and CFD is used to interpret the free stream optical diagnostic measurements.
Document ID
19920071556
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Cavolowsky, John A.
(NASA Ames Research Center Moffett Field, CA, United States)
Loomis, Mark P.
(MCAT Institute San Jose, CA, United States)
Bogdanoff, David W.
(NASA Ames Research Center Moffett Field, CA, United States)
Zambrana, Horacio A.
(Eloret Institute Palo Alto, CA, United States)
Newfield, Mark E.
(NASA Ames Research Center Moffett Field, CA, United States)
Tam, Tim C.
(NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
August 15, 2013
Publication Date
July 1, 1992
Subject Category
Research And Support Facilities (Air)
Report/Patent Number
AIAA PAPER 92-3810
Accession Number
92A54180
Distribution Limits
Public
Copyright
Other

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