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Nozzle wall roughness effects on free-stream noise and transition in the pilot low-disturbance tunnelAn investigation at Mach 3.5 into the effects of nozzle wall roughness on free stream pressure fluctuations and cone transition Reynolds numbers was conducted in the pilot low disturbance tunnel at the Langley Research Center. Nozzle wall roughness caused by either particle deposits or imperfections in surface finish increased free stream noise levels and reduced the transition Reynolds numbers on a cone mounted in the test rhombus.
Document ID
19850026042
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Creel, T. R., Jr. (NASA Langley Research Center Hampton, VA, United States)
Beckwith, I. E. (NASA Langley Research Center Hampton, VA, United States)
Chen, F. J. (High Technology Corp.)
Date Acquired
September 5, 2013
Publication Date
September 1, 1985
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
NASA-TM-86389
L-15903
NAS 1.15:86389
Report Number: NASA-TM-86389
Report Number: L-15903
Report Number: NAS 1.15:86389
Accession Number
85N34355
Funding Number(s)
PROJECT: RTOP 505-31-13-06
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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