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- W2066880004 abstract "While conclusions that may be drawn on the basis of these solutions are strictly valid only for incompressible laminar flow, they can be plausibly assumed to apply to a much larger class of flows. We note that the differences between the various approximations and the full equations decrease with increasing Reynolds number as expected. Since most aerodynamically significant flows are at high Reynolds numbers, the error introduced by the approximation to the governing equations will tend to be small and will certainly be insignificant relative to the errors introduced by the turbulence model. Compressibility effects should not alter the present conclusions insofar as viscous .effects are concerned, and the direct effects of shock waves and normal pressure gradients within the boundary layer as sources of error should be relatively small for moderate Mach numbers. In this regard, the recent comparisons of Navier-Stokes and thinlayer solutions for supersonic corner flow are informative. For any flow, or region of flow, for which viscous-inviscid interaction effects are small, classical boundary-layer equations will provide a satisfactory description of the viscous flow at a fraction of the computational cost of any higher approximation. For flows with significant viscous-inviscid interaction, as long as they are boundary-layer-like, i.e., v/u <1, coupled boundary-layer/inviscid equations will provide an adequate flow description." @default.
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- W2066880004 date "1983-12-01" @default.
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- W2066880004 title "Decomposition of a disturbance in parallel shear flows" @default.
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