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Free flight determination of boundary layer transition on small scale cones in the presence of surface ablationTo assess the possibility of achieving extensive laminar flow on conical vehicles during hyperbolic entry, the Ames Research Center has had an ongoing program to study boundary-layer transition on ablating cones. Boundary layer transition results are presented from ballistic range experiments with models that ablated at dimensionless mass transfer rates comparable to those expected for full scale flight at speeds up to 17 km/sec. It was found possible to measure the surface recession and hence more accurately identify regions of laminar, transitional, and turbulent flow along generators of the recovered cones. Some preliminary results using this technique are presented.
Document ID
19730003566
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Wilkins, M. E.
(NASA Ames Research Center Moffett Field, CA, United States)
Chapman, G. T.
(NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
September 2, 2013
Publication Date
August 3, 1972
Subject Category
Fluid Mechanics
Report/Patent Number
NASA-TM-X-68867
Accession Number
73N12293
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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