Unsteady Navier-Stokes computations past oscillating delta wing at high incidence

The unsteady, compressible, thin-layer, Navier-Stokes equations, written in the moving frame of reference for the flow relative motion, are solved for the unsteady supersonic flow around a round-edged delta wing. For supersonic flow, a local conical flow solution has been obtained from the three-dimensional equations. Pseudotime stepping is used for the steady flow problem; while time-accurate stepping is used for the unsteady flow problem. The computational scheme is an implicit, approximately factored, finite-volume scheme, which uses implicit and explicit dissipation terms. The scheme is verified for the steady flow solution. The scheme is then applied to a delta wing undergoing rolling oscillation at a reduced frequency of 1.337 with 15-deg maximum amplitude about a mean angle of attack of 10 deg for a Mach number of 2 and a Reynolds number of 0.5 x 10 6.

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