Abstract
A method for the evaluation of blockage interference for propeller models in a perforated-wall wind tunnel is presented. The correction procedure, based on a Fourier solution for the Dirichlet problem inside a cylindrical flow domain, uses boundary data obtained from pressure measurements along the wind-tunnel walls and a farfield representation of the propeller. The radial contraction of the slip stream is modeled by a sink, whose strength and location are evaluated from the measured thrust and power using axial momentum theory. An iterative procedure is developed for a compressible slip stream, using the Rankine-Froude theory as the first approximation. The equations describing the discontinuity of momentum and energy across the propeller disk are discussed and solved similarly to those describing a discontinuity across a normal shock.
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