NASA Logo

NTRS - NASA Technical Reports Server

Back to Results
A fan pressure ratio correlation in terms of Mach number and Reynolds number for the Langley 0.3 meter transonic cryogenic tunnelCalibration data for the two dimensional test section of the Langley 0.3 Meter Transonic Cryogenic Tunnel were used to develop a Mach number-Reynolds number correlation for the fan pressure ratio in terms of test section conditions. Well established engineering relationships combined to form an equation which is functionally analogous to the correlation. A geometric loss coefficient which is independent of Reynolds number or Mach number was determined. Present and anticipated uses of this concept include improvement of tunnel control schemes, comparison of efficiencies for operationally similar wind tunnels, prediction of tunnel test conditions and associated energy usage, and determination of Reynolds number scaling laws for similar fluid flow systems.
Document ID
19810001497
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Lawing, P. L. (NASA Langley Research Center Hampton, VA, United States)
Adcock, J. B. (NASA Langley Research Center Hampton, VA, United States)
Ladson, C. L. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 4, 2013
Publication Date
November 1, 1980
Subject Category
Aerodynamics
Report/Patent Number
L-13713
NASA-TP-1752
Report Number: L-13713
Report Number: NASA-TP-1752
Accession Number
81N10005
Funding Number(s)
PROJECT: RTOP 505-31-53-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

Related Records

There are no records associated with this record.
No Preview Available