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Navier-Stokes calculations on multi-element airfoils using a chimera-based solverA study of Navier-Stokes calculations of flows about multielement airfoils using a chimera grid approach is presented. The chimera approach utilizes structured, overlapped grids which allow great flexibility of grid arrangement and simplifies grid generation. Calculations are made for two-, three-, and four-element airfoils, and modeling of the effect of gap distance between elements is demonstrated for a two element case. Solutions are obtained using the thin-layer form of the Reynolds averaged Navier-Stokes equations with turbulence closure provided by the Baldwin-Lomax algebraic model or the Baldwin-Barth one equation model. The Baldwin-Barth turbulence model is shown to provide better agreement with experimental data and to dramatically improve convergence rates for some cases. Recently developed, improved farfield boundary conditions are incorporated into the solver for greater efficiency. Computed results show good comparison with experimental data which include aerodynamic forces, surface pressures, and boundary layer velocity profiles.
Document ID
19940013949
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Jasper, Donald W.
(McDonnell Aircraft Co. Saint Louis, MO, United States)
Agrawal, Shreekant
(McDonnell Aircraft Co. Saint Louis, MO, United States)
Robinson, Brian A.
(McDonnell Aircraft Co. Saint Louis, MO, United States)
Date Acquired
August 16, 2013
Publication Date
September 1, 1993
Publication Information
Publication: AGARD, High-Lift System Aerodynamics
Subject Category
Aerodynamics
Accession Number
94N18422
Distribution Limits
Public
Copyright
Other
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