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Numerical Simulation For Supersonic InletsFlows calculated for realistic engine-inlet conditions. Computer code LAPIN, large-perturbation inlet, developed to analyze large-perturbation, transient-flow fields in supersonic inlets. Robust, quick-running code capable of solving unsteady quasi-one-dimensional, inviscid-flow problems in mixed subsonic and supersonic regimes for inlets. Approach based upon quasi-one-dimensional, inviscid, unsteady formulation including engineering models of unstart/restart, bleed, bypass, and geometrical effects. Numerical solution of governing time-dependent equations of motion accomplished through shock-capturing, finite-difference algorithm. Program written in FORTRAN IV.
Document ID
19870000547
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Tech Brief
Authors
Varner, M. O.
(Sverdrup Technology, Inc.)
Martindale, W. R.
(Sverdrup Technology, Inc.)
Phares, W. J.
(Sverdrup Technology, Inc.)
Kneile, K. R.
(Sverdrup Technology, Inc.)
Adams, J. C., Jr.
(Sverdrup Technology, Inc.)
Date Acquired
August 13, 2013
Publication Date
November 1, 1987
Publication Information
Publication: NASA Tech Briefs
Volume: 11
Issue: 10
ISSN: 0145-319X
Subject Category
Mechanics
Report/Patent Number
LEW-14324
Accession Number
87B10547
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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