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The response of a laminar boundary layer in supersonic flow to small amplitude progressive wavesThe effect of a small amplitude progressive wave on the laminar boundary layer on a semi-infinite flat plate, due to a uniform supersonic freestream flow, is considered. The perturbation to the flow divides into two streamwise zones. In the first, relatively close to the leading edge of the plate, on a transverse scale comparable to the boundary layer thickness, the perturbation flow is described by a form of the unsteady linearized compressible boundary layer equations. In the freestream, this component of flow is governed by the wave equation, the solution of which provides the outer velocity conditions for the boundary layer. This system is solved numerically, and also the asymptotic structure in the far downstream limit is studied. This reveals a breakdown and a subsequent second streamwise zone, where the flow disturbance is predominantly inviscid. The two zones are shown to match in a proper asymptotic sense.
Document ID
19890011826
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Duck, Peter W.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 5, 2013
Publication Date
March 1, 1989
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
E-4663
NASA-TM-101965
NAS 1.15:101965
ICOMP-89-6
Report Number: E-4663
Report Number: NASA-TM-101965
Report Number: NAS 1.15:101965
Report Number: ICOMP-89-6
Accession Number
89N21197
Funding Number(s)
PROJECT: RTOP 505-62-27
CONTRACT_GRANT: NASA ORDER C-99066-G
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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