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Unsteady Navier-Stokes computations over airfoils using both fixed and dynamic meshesA finite volume implicit approximate factorization method which solves the thin layer Navier-Stokes equations was used to predict unsteady turbulent flow airfoil behavior. At a constant angle of attack of 16 deg, the NACA 0012 airfoil exhibits an unsteady periodic flow field with the lift coefficient oscillating between 0.89 and 1.60. The Strouhal number is 0.028. Results are similar at 18 deg, with a Strouhal number of 0.033. A leading edge vortex is shed periodically near maximum lift. Dynamic mesh solutions for unstalled airfoil flows show general agreement with experimental pressure coefficients. However, moment coefficients and the maximum lift value are underpredicted. The deep stall case shows some agreement with experiment for increasing angle of attack, but is only qualitatively comparable past stall and for decreasing angle of attack.
Document ID
19890009881
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Rumsey, Christopher L. (NASA Langley Research Center Hampton, VA, United States)
Anderson, W. Kyle (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 5, 2013
Publication Date
February 1, 1989
Publication Information
Publication: Transonic Unsteady Aerodynamics and Aeroelasticity 1987, Part 2
Subject Category
Aerodynamics
Accession Number
89N19252
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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