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Two inviscid computational simulations of separated flow about airfoilsTwo inviscid computational simulations of separated flow about airfoils are described. The basic computational method is the line relaxation finite-difference method. Viscous separation is approximated with inviscid free-streamline separation. The point of separation is specified, and the pressure in the separation region is calculated. In the first simulation, the empiricism of constant pressure in the separation region is employed. This empiricism is easier to implement with the present method than with singularity methods. In the second simulation, acoustic theory is used to determine the pressure in the separation region. The results of both simulations are compared with experiment.
Document ID
19760054059
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Barnwell, R. W. (NASA Langley Research Center Hampton, Va., United States)
Date Acquired
August 8, 2013
Publication Date
July 1, 1976
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 76-379
Meeting Information
Meeting: Fluid and Plasma Dynamics Conference
Location: San Diego, CA
Start Date: July 14, 1976
End Date: July 16, 1976
Sponsors: American Institute of Aeronautics and Astronautics
Accession Number
76A37025
Distribution Limits
Public
Copyright
Other

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