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Interacting boundary-layer solutions for laminar separated flow past airfoilsNumerical solutions of the interacting laminar boundary layer equations are presented for two symmetric airfoils at zero incidence: the NACA 0012 and the NACA 66 sub 3-108 airfoils. The potential flow was computed using Carlson's code, and viscous interaction was treated following a Hilbert integral scheme due to Veldman. Effects of various grid parameters are studied, and pressure and skin friction distributions are compared at several Reynolds numbers. For the NACA 0012 airfoil, Reynolds number is varied from a value just below separation (R sub N = 3000) to a value for which extensive separation occurs (R sub N = 100,000). For the 66 sub 3-018 airfoil, results are given at intermediate values (R sub N - 10,000 and 40,000). The method fails to converge for greater values of Reynolds number, corresponding to the development of very thin well separated shear layers where transition to turbulence would occur naturally.
Document ID
19840008072
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Burggraf, O. R.
(Ohio State Univ. Columbus, OH, United States)
Date Acquired
September 4, 2013
Publication Date
January 1, 1984
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.26:172287
NASA-CR-172287
Accession Number
84N16140
Funding Number(s)
PROJECT: RTOP 505-31-23-06
CONTRACT_GRANT: NSG-1622
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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