In the present study the supersonic flow over rigid and flexible parachute modes were studied by numerically solving the compressible Navier-Stokes equations at a freestream Mach number of 2. The parachute system employed here consists of two elements: a capsule and a canopy. For the three-dimensional rigid case, two models were considered: Model A and Model B. The former is the same model as the experiment, where the canopy is connected with the capsule by a rod, and the whole system is supported by another rod, while the latter does not have these rods. On the other hand, for the flexible case, two-dimensional and axisymmetric flexible parachute models were adopted, where the immersed boundary method was applied to capture the deformation of the canopy. The objective of the present study is to analyze the effects of aerodynamic interaction such as wake/shock and shock/shock interactions on the flow field and examine the difference in flow behaviour between the rigid and flexible cases. As a result, the numerical and experimental results show good agreement in the case of model A. In addition, by reducing the trailing distance between the capsule and canopy, the complicated wake/aftershock and foreshock/aftershock interactions were observed in the 3D rigid and axisymmetric flexible cases. In the unsteady flow pulsation mode, the bow shock formed ahead of the capsule periodically inflates and laterally expands, taking a hemispherical shape. This is caused by upstream propagation and lateral expansion of the complicated wake/aftershock and foreshock/aftershock interaction systems.
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