A wind tunnel interference assessment concept which presents a rational predictive means of wall interference analysis is evaluated. The procedure consists of employing as an outer boundary condition an experimentally-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 implementation. The procedure relates directly to the correctable-interference wind tunnel concept recently suggested. (Author)