Navier-Stokes computations of vortical flows over low-aspect-ratio wings

An upwind-biased finite-volume algorithm is applied to the low-speed laminar flow over a low-aspect-ratio delta wing from 0 to 40 deg angle of attack. The differencing is second-order accurate spatially and a multigrid algorithm is used to promote convergence to the steady state. The results compare...

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Bibliographic Details
Published in:AIAA journal 1990-02, Vol.28 (2), p.205-212
Main Authors: Thomas, James L, Krist, Sherrie Taylor, Anderson, W. Kyle
Format: Article
Language:English
Subjects:
Aerodynamics
Applied fluid mechanics
Exact sciences and technology
finite volume method
Fluid dynamics
Fundamental areas of phenomenology (including applications)
laminar flow
Physics
vortices
wings
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Summary:An upwind-biased finite-volume algorithm is applied to the low-speed laminar flow over a low-aspect-ratio delta wing from 0 to 40 deg angle of attack. The differencing is second-order accurate spatially and a multigrid algorithm is used to promote convergence to the steady state. The results compare well with the detailed experiments of Hummel and others for an Re sub(L) of 0.95 x 10 super(6). The predicted maximum lift coefficient of 1.10 at 35 deg angle of attack agrees closely with the measured maximum lift of 1.06 at 33 deg. At 40 deg angle of attack, a bubble type of vortex breakdown is evident in the computations, extending from 0.6 of the root chord to just downstream of the trailing edge.
ISSN:0001-1452
1533-385X
DOI:10.2514/3.10376