A three-dimensional Euler aerodynamic method based on a finite-volume, multistage time-stepping algorithm is used to simulate free vortices generated by flow separation along the edges of swept, slender wings at moderate to high angles of attack. Computed results for a cropped-delta wing, an arrow wing, and a strake-wing-body configuration are correlated with experimental data and, for cropped-delta wing, with predictions of other numerical methods also. The flow is impulsively started and the vortices are automatically captured. The following two issues are specifically addressed: 1) sensitivity of the solutions to artificial viscosity and 2) effect of grid density on the results. Relatively small changes in the subsonic solutions are noticed with variations in the magnitude of artificial viscosity parameters and grid density. The correlations presented here provide an added measure of confidence in computational simulations using the Euler equations. The present investigation also raises some new issues related to vortex instabilities.

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