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An LU implicity scheme for high speed inlet analysisA numerical method is developed to analyze the inviscid flowfield of a high speed inlet by the solution of the Euler equations. The lower-upper implicit scheme in conjunction with adaptive dissipation proves to be an efficient and robust nonoscillatory shock capturing technique for high Mach number flows as well as for transonic flows.
Document ID
19860014092
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Yoon, S. (Sverdrup Technology, Inc. Cleveland, OH, United States)
Jameson, A. (Princeton Univ. N.J., United States)
Date Acquired
September 5, 2013
Publication Date
April 1, 1986
Subject Category
Aerodynamics
Report/Patent Number
NASA-CR-175098
AIAA PAPER 86-1520
NAS 1.26:175098
Report Number: NASA-CR-175098
Report Number: AIAA PAPER 86-1520
Report Number: NAS 1.26:175098
Meeting Information
Meeting: Joint Propulsion Conference
Location: Huntsville, AL
Country: United States
Start Date: June 16, 1986
End Date: June 18, 1986
Sponsors: SAE, ASEE, AIAA, ASME
Accession Number
86N23563
Funding Number(s)
CONTRACT_GRANT: NAS3-24105
PROJECT: RTOP 505-62-21
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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