Author(s) :

Aarushi Sanganeria.

Volume/Issue :

Abstract :

The Mars Sample Retrieval mission demands high-performance parachutes capable of surviving supersonic deceleration in Mars’ low-density atmosphere, specifically for the Lander. This study evaluates the suitability of a Ringsail parachute through computational fluid dynamics (CFD) simulations at supersonic (500 ms-1), low density (0.02 kgm-3) conditions. Velocity magnitude analysis revealed significant flow separation and turbulent wake formation. Stagnation zones posed localized stress risks, while asymmetric vorticity suggested susceptibility to collapse. This paper used computational f luid dynamics to evaluate the performance of a Ringsail parachute designed in Fusion360 in Martian atmospheric conditions through analysing lift and drag forces and coefficient of drag. The results are then validated against a previous study regarding the performance of Supersonic Ringsail Parachutes on Mars. Future work could explore transient inflation dynamics, material thermal limits, and varying porosity.