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Transverse injection into Mach 2 flow behind a rearward-facing step - A 3-D, compressible flow test case for hypersonic combustor CFD validationA spatially-complete data set of the important primitive flow variables is presented for the complex, nonreacting, 3D unit combustor flow field employing transverse injection into a Mach 2 flow behind a rearward-facing step. A unique wind tunnel facility providing the capability for iodine seeding was built specifically for these measurements. Two optical techniques based on laser-induced-iodine fluorescence were developed and utilized for nonintrusive, in situ flow field measurements. LDA provided both mean and fluctuating velocity component measurements. A thermographic phosphor wall temperature measurement technique was developed and employed. Data from the 2D flow over a rearward-facing step and the complex 3D mixing flow with injection are reported.
Document ID
19920049069
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Mcdaniel, James C.
(Virginia, University Charlottesville, United States)
Fletcher, Douglas G.
(NASA Ames Research Center Moffett Field, CA, United States)
Hartfield, Roy J.
(NASA Ames Research Center Moffett Field, CA, United States)
Hollo, Steven D.
(Virginia, University Charlottesville, United States)
Date Acquired
August 15, 2013
Publication Date
December 1, 1991
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
AIAA PAPER 91-5071
Accession Number
92A31693
Funding Number(s)
CONTRACT_GRANT: NAS1-18471
CONTRACT_GRANT: NAG1-795
CONTRACT_GRANT: NAG1-373
Distribution Limits
Public
Copyright
Other

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