This paper describes a series of steady and time-dependent pressure measurements on a half-model of a rectangular wing of aspect ratio 4. The wing was mounted on a half-body attached to a sidewall of the RAE 8 x 8 ft wind tunnel and the tests were made at Mach numbers of 0·20, 0·42, 0·70, 0·80 and 0·85 with fixed transition and a Reynolds number of about 2·5 x 106 at the highest Mach number. The wing was oscillated about its mid-chord axis at four frequencies giving frequency parameters up to 1·15 at M = 0·20 and 0·25 at M = 0·85. The static angle of incidence was varied from –10° to + 10°.

Selected mean and oscillatory measurements are offered as a challenge to computational fluid dynamicists for this simple three-dimensional configuration. Comparisons are made with calculations by means of subsonic linearised theory and recent transonic small perturbation methods. The measurements are of particular interest at transonic speeds, where both attached and incipient separated flows are considered.

An analysis is presented of the output of a pressure probe, comprised essentially of four yawmeters, which was designed to yield vorticity information.

It is shown that if the probe is utilised in flows which have vorticity dominated by variation of either the direction or the magnitude of the velocity then the probe output may be easily related to vorticity. It is argued that such flows should be readily recognised, and they include many situations of interest involving vortex flows, boundary layers and wakes.

Earlier work had already demonstrated that the probe is useful in exploring regions of predominantly streamwise vorticity. The present work shows a result with the probe used in a boundary layer flow where the vorticity is nearly normal to the local flow.

Use of the probe in unsteady flow is briefly examined.