Navier-Stokes computations of vortical flows over low aspect ratio wingsAn upwind-biased finite-volume algorithm is applied to the low-speed flow over a low aspect ratio delta wing from zero to forty degrees 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 (1983) and others for a Re(L) of 0.95 x 10 to the 6th. The predicted maximum lift coefficient of 1.10 at thirty-five degrees angle of attack agrees closely with the measured maximum lift of 1.06 at thirty-three degrees. At forty degrees 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.
Document ID
19870035211
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Thomas, J. L. (NASA Langley Research Center Hampton, VA, United States)
Taylor, S. L. (NASA Langley Research Center Hampton, VA, United States)
Anderson, W. K. (NASA Langley Research Center Hampton, VA, United States)