The problem of extracting static pressure fields on and away from flow boundaries in complex flows, is considered. Given the correct velocity field in steady incompressible flow, an assumption of constant or known stagnation pressure allows finding the static pressure. This gives an upper bound on static pressure, and is in fact close to the real answer. The technique developed here is to start with the measured, ensemble-averaged 3-component velocity field in a periodic flow. The static pressure field computed from this velocity field in incompressible flow can be used along with the velocity field as the starting guess of a solution in a Navier-Stokes solver. The method is applied to the bottom surface near the sharp edge of a rotating rotor blade in the reverse flow domain encountered at high advance ratio in a wind tunnel. The drop in stagnation pressure along given streamlines even through the sharp-edge vortex, is shown to be very small, so that the effect on the static pressure estimate is minor. The pressure field successfully explains some features that could not otherwise be explained.

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