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Crossflow in two-dimensional asymmetric nozzlesAn experimental investigation of the crossflow effects in three contoured, two-dimensional asymmetric nozzles is described. The data were compared with theoretical predictions of nozzle flow by using an inviscid method of characteristics solution and two-dimensional turbulent boundary-layer calculations. The effect of crossflow as a function of the nozzle maximum expansion angle was studied by use of oil-flow techniques, static wall-pressure measurements, and impact-pressure surveys at the nozzle exit. Reynolds number effects on crossflow were investigated.
Document ID
19750021292
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Technical Note (TN)
Authors
Sebacher, D. I. (NASA Langley Research Center Hampton, VA, United States)
Lee, L. P. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 3, 2013
Publication Date
August 1, 1975
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
NASA-TN-D-7999
L-10072
Report Number: NASA-TN-D-7999
Report Number: L-10072
Accession Number
75N29365
Funding Number(s)
PROJECT: RTOP 505-05-41-03
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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