Static-force tests were conducted at Mach numbers from 1.5 through 6 on rigid models of a supersonic X-2 parachute and two conical decelerators in the wake of cone-cylinder and ejection-seat forebodies. Surface pressure data were also obtained on the conical decelerators. The tests were made at decelerator angles of attack from -8 to 8 deg at free-stream dynamic pressures of 0.5, 1.0, 1.5, and 2.0 psia. The decelerators were positioned at various axial stations in the forebody wake, and selected configurations were tested in the free stream (no forebody). The data presented show how a rigid model of a flexible parachute can be used to obtain performance data in terms of static stability and drag coefficients. Agreement was obtained in axial-force coefficient for a rigid parachute model with a previously tested flexible model of the same configuration deployed behind the same forebody.