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A compressible solution of the Navier-Stokes equations for turbulent flow about an airfoilA compressible time dependent solution of the Navier-Stokes equations including a transition turbulence model is obtained for the isolated airfoil flow field problem. The equations are solved by a consistently split linearized block implicit scheme. A nonorthogonal body-fitted coordinate system is used which has maximum resolution near the airfoil surface and in the region of the airfoil leading edge. The transition turbulence model is based upon the turbulence kinetic energy equation and predicts regions of laminar, transitional, and turbulent flow. Mean flow field and turbulence field results are presented for an NACA 0012 airfoil at zero and nonzero incidence angles of Reynolds number up to one million and low subsonic Mach numbers.
Document ID
19790024990
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Shamroth, S. J. (Scientific Research Associates, Inc. Glastonbury, CT, United States)
Gibeling, H. J. (Scientific Research Associates, Inc. Glastonbury, CT, United States)
Date Acquired
September 3, 2013
Publication Date
October 1, 1979
Publication Information
Publisher: NASA
Subject Category
Aerodynamics
Report/Patent Number
NASA-CR-3183
Accession Number
79N33161
Funding Number(s)
CONTRACT_GRANT: NAS1-15214
PROJECT: RTOP 505-10-23-07
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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