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Boundary-Layer Code For Supersonic CombustionHUD is integral computer code based on Spaulding-Chi method for predicting development of boundary layers in laminar, transitional, and turbulent regions of flows on two-dimensional or axisymmetric bodies. Approximates nonequilibrium velocity profiles as well as local surface friction in presence of pressure gradient. Predicts transfer of heat in turbulent boundary layer in presence of high axial presure gradient. Provides for pressure gradients both normal and lateral to surfaces. Also used to estimate requirements for cooling scramjet engines. Because of this capability, HUD program incorporated into several scramjet-cycle-performance-analysis codes, including SCRAM (ARC-12338) and SRGULL (LEW-15093). Written in FORTRAN 77.
Document ID
19940000264
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Tech Brief
Authors
Pinckney, S. Z.
(Langley Research Center)
Walton, J. T.
(NASA Lewis Research Center, Cleveland, OH.)
Date Acquired
August 16, 2013
Publication Date
May 1, 1994
Publication Information
Publication: NASA Tech Briefs
Volume: 18
Issue: 5
ISSN: 0145-319X
Subject Category
Mechanics
Report/Patent Number
LEW-15163
Accession Number
94B10264
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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