The potential value of controlled boundary-layer removal from the wall of a nozzle for low-density hypersonic flow was investigated in a brief experimental program. A particular objective was the achievement of sufficient control over boundary-layer thickness to enable a contoured nozzle to be operated under off-design conditions without excessive deterioration of flow uniformity. The nozzle contour was greatly influenced by boundary-layer thickness. Boundary-layer removal involved suction through perforated walls where local nozzle static pressures exceeded the pressure in the large tank which enclosed the nozzle and test section.