Classification of supersonic flow over a rigid parachute model with suspension lines

The supersonic wind tunnel tests using a rigid parachute model were conducted for Mach numbers ranging from 2.0 to 3.0. The rigid model consists of suspension lines and a riser between the forebody and rear body, and the effect of these suspension lines was investigated. Three characteristic flow modes, namely, high-pressure, low-pressure, and attachment modes, were observed. These three modes were classified on the basis of the shape and position of the apex of the shock wave. In addition, the non-dimensional pressure observed at the center of the canopy varied according to the pressure mode produced. The emergence of each pressure mode depended on the parameters, namely, freestream Mach number, trailing distance, and distance between the bundling point and rear body. Pressure-mode transitions were observed when specific conditions and configuration of the parameters were achieved.