Drag, Performance Characteristics, and Pressure Distributions of Several Rigid Aerodynamic Decelerators at Mach Numbers from 0.2 to 5

摘要

Static force and pressure distribution tests were conducted at Mach numbers from 0.2 to 5.0 on rigid models of several aerodynamic decelerators in the wake of three types of forebodies. The tests were conducted at decelerator pitch angles from -8 to 8 deg at nominal 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 wake of the forebodies, and selected configurations were tested in the free stream (no forebodies). Data are presented showing the effects of Mach numbers, decelerator pitch angle, and location in the wake on the drag and stability of various decelerator configurations. The pressure data support the measured force data and show large fluctuations in the canopy internal pressure on the supersonic X-2 parachute design. (Author)