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Flow visualization in a cryogenic wind tunnel using holographyResults of holographic flow visualization from tests made in the Langley 0.3 meter transonic cryogenic tunnel are presented. The tunnel was operated over a temperature range from 100 to 300 K and a pressure range from 1.1 to 4 atm. Interferometry at the facility may be of limited use at the low temperature high pressure conditions because of the jumbled nature of the reference fringes. The shadowgraph technique appears to be the best means of visualizing shocks at these high density conditions. The spot size at the focus of the reconstructed beams was measured and used as an indicator of density fluctuations in the flow field. These density fluctuations appear to be caused by temperature fluctuations of the test gas which are relatively independent of tunnel conditions.
Document ID
19830004125
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Burner, A. W. (NASA Langley Research Center Hampton, VA, United States)
Goad, W. K. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 4, 2013
Publication Date
November 1, 1982
Subject Category
Instrumentation And Photography
Report/Patent Number
NASA-TM-84556
L-15510
NAS 1.15:84556
Accession Number
83N12395
Funding Number(s)
PROJECT: RTOP 505-31-53-06
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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