Abstract
Three-dimensional viscous flow calculations are performed for a swept NACA 0012 wing mounted inside a wind tunnel for which detailed experimental data are available. A Runge-Kutta time-stepping scheme is used for obtaining steady-state solutions to the thin-layer Navier-Stokes equations. The effect of the wind-tunnel sidewall boundary layer on the flow pattern over the wing surface, particularly in the vicinity of the wing/wall juncture, is found to be significant. The computed results agree well with the data over a major portion of the wing. The extent of flow separation is underpredicted on the wing, which is attributed to the use of an equilibrium turbulence model.
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