Abstract
A correction method is described for half-model tests using wall pressures measured by longitudinal static pressure tubes and measured model forces. The Dirichlet problem for the Mach number correction is solved by a doublet-panel method and the flow angle corrections are obtained from the irrotational flow conditions. The method is applied to a transport aircraft half-model tested in the NAE perforated-wall wind tunnel. The Mach number and angle-of-attack corrections are presented as contour plots, allowing analysis of the effects of wallinduced gradients. In the range of normal operating lift coefficients, the corrected drag polar is shown to correlate well with data from full-model wind-tunnel tests and from the flight test aircraft.
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