Computational Study on Rigid Disk-Gap-Band Supersonic Parachute Aerodynamics
In Mars, supersonic parachutes have been used as a decelerator at around Mach 2. In order to stabilize the parachute, NASA proposed a supersonic parachute equipped with a gap and a vent, called disk-gap-band (DGB) supersonic parachute. However, it is not fully investigated how its surrounding flow field and its aerodynamics are affected by the gap and the vent (a small ventilation hole at a stagnation point). In this study, a computational study has been carried out on the aerodynamics of rigid-body-modeled parachutes. Results indicate that computed drag coefficient is in good agreement with the experimental data. Moreover, it is observed that reduction of drag per opening area by the vent is greater than that by the gap. Two factors are considered for this reduction: (1) the vortices around the jet from the gap and (2) the vent location at a stagnation point.
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