Phase-locked, steady and unsteady, surface pressure measurements were made on the vanes of a compressible cascade, for inlet Mach numbers up to —0.7. The cascade vanes were production hardware stator vanes from an AlliedSignal F109 turbofan engine. Data are presented from which it may be concluded that the cascade produces reasonably good two-dimensional flow through the vane row. Unsteady forcing within the cascade can be produced either upstream or downstream of the vane row. In the present paper, flow unsteadiness in the cascade was produced using shedding from circular cylinders positioned at a distance equal to 80 % vane chords downstream of the vane row. This rearward forcing of the vane row resulted in unsteady surface pressures of the same order as those produced in similar experiments with forward forcing. Decomposition of the ensembled, phase-locked, pressure-response signals for rearward forcing provided insight into both the nature of the unsteady disturbance and the physics of its propagation within the vane row.