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Numerical solution of flowfields behind rectangular wingsThe numerical solution of flow fields behind rectangular wings is described. Subjects discussed are: (1) evaluation of various differencing methods applied to the hyperbolic partial differential equations encountered in gas dynamics, (2) application of the numerical differencing techniques to the wedge flow, two dimensional shock reflection for the three dimensional finite thickness wing at zero degrees angle of attack, and (3) calculation of preliminary results for wedge flows using optimum differencing methods.
Document ID
19720014348
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Anderson, D. (Iowa State Univ. of Science and Technology Ames, IA, United States)
Vogel, J. (Iowa State Univ. of Science and Technology Ames, IA, United States)
Date Acquired
August 6, 2013
Publication Date
July 1, 1971
Subject Category
Aerodynamics
Report/Patent Number
NASA-CR-126214
ISU-ERI-AMES-71015
Report Number: NASA-CR-126214
Report Number: ISU-ERI-AMES-71015
Accession Number
72N21998
Funding Number(s)
PROJECT: PROJ. 859-S
OTHER: NGR-16-002-029
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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