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Base pressure in laminar supersonic flow.An asymptotic description is proposed for supersonic laminar flow over a wedge or a backward-facing step, for large Reynolds number and for a base or step height which is small compared with the boundary-layer length. The analysis is carried out for adiabatic wall conditions and a viscosity coefficient proportional to temperature. In a particular limit corresponding to a very thick boundary layer, a similarity law is obtained for the base pressure. For a thinner boundary layer an asymptotic form for the base pressure is obtained which shows the dependence on the parameters explicitly and which permits good agreement with experiment. This latter result is based on an inviscid-flow approximation for the corner expansion and for reattachment with viscous forces important primarily in a thin sublayer about the dividing streamline. A prediction of the pressure distribution at reattachment is given and the result is compared with experimental pressure distributions.
Document ID
19730060512
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Messiter, A. F.
(Michigan, University Ann Arbor, Mich., United States)
Hough, G. R.
(NASA Ames Research Center Moffett Field, Calif., United States)
Feo, A.
(Instituto Nacional de Tecnica Aeroespacial Madrid, Spain)
Date Acquired
September 2, 2013
Publication Date
September 18, 1973
Publication Information
Publication: Journal of Fluid Mechanics
Volume: 60
Subject Category
Aerodynamics
Report/Patent Number
AROD-7324-4-E
AD-785786
Accession Number
73A45314
Funding Number(s)
CONTRACT_GRANT: DAHC04-68-C-0033
Distribution Limits
Public
Copyright
Other

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