A wind tunnel interference assessment concept that presents a rational predictive means of wall interference analysis is evaluated. The procedure consists of employing as an outer boundary condition an experimentall y measured pressure distribution along a convenient control surface located inward from the actual tunnel walls. Attention has been focused on axisymmetric flows in the transonic regime, where tunnel interference is high and where the experimentally measured conditions on the control surface are of mixed subsonic/supersonic type. Based on the transonic small-disturbance equation, results for surface and near-flow field pressure distributions are presented for a variety of different slender-body shapes. These calculations indicate both the accuracy of the procedure as well as its ease of implementatio n. The procedure relates directly to the correctable-interference wind-tunnel concept recently suggested.