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Calculation of three-dimensional, inviscid, supersonic, steady flowsA detailed description of a computational program for the evaluation of three dimensional supersonic, inviscid, steady flow past airplanes is presented. Emphasis was put on how a powerful, automatic mapping technique is coupled to the fluid mechanical analysis. Each of the three constituents of the analysis (body geometry, mapping technique, and gas dynamical effects) was carefully coded and described. Results of computations based on sample geometrics and discussions are also presented.
Document ID
19820008174
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Moretti, G. (Polytechnic Inst. of New York Brooklyn, NY, United States)
Date Acquired
September 4, 2013
Publication Date
December 1, 1981
Subject Category
Aerodynamics
Report/Patent Number
NASA-CR-165110
POLY-M/AE-81-25
Accession Number
82N16047
Funding Number(s)
CONTRACT_GRANT: NSG-1248
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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