An experimental program was conducted at NASA Langley Research Center, in Hampton Virginia, that included development and evaluation of an operational facility for wall drag measurement and evaluation of the total drag of various wall configurations. The drag of three possible supersonic combustor wall configurations was measured to determine if reduction in skin friction and/or wave drag could be achieved through the use of cavities, vented cavities, and/or mass addition. Data are presented herein as average drag force, wall static pressure distributions and focusing schlieren images. The experimental model consisted of a series of interchangeable aluminum plates attached to an air-bearing suspension system. The system was equipped with load cells that measured forces up to 10 pounds in the drag direction only. The plates were exposed to a Mach 2 air stream at a total pressure of 115 psia. This flow field contained a train of relatively weak, unsteady, reflecting shock waves that were produced by the Mach 2 nozzle and plenum chamber assembly. Mass addition was successfully employed to alter the plate drag in both the transpiration and cavity configurations. Three plate configurations were tested: a flat plate, a plate with air transpiration, and a cavity plate equipped for the introduction of bleed air into the cavity. The resulting data base consists of drag data at Mach 2 for a standard flat plate, and two wall configurations tested with bleed mass flow rates ranging from 0.00 to 0.06 lbm/sec. The experimental wall static pressure distributions and the focusing schlieren images are shown to compare favorably with the CAN-DO computer analysis results. / Master of Science