The article presents the results of a numerical study of the spatial non-stationary flow structure arising during supersonic motion in the atmosphere of the descent vehicle and parachute located in its vortex wake. The cases of the vehicle at angle of attack and various location of the parachute in relation to the vehicle are considered. For different distances between vehicle and parachute the patterns of the spatial non-stationary vortex structure of the flow occurring between them and in the near wake of the parachute are given. The significant influence of the distance between the vehicle and the parachute on the flow structure and force characteristics effect of the flow on the parachute is shown. Data on the influence of attack angle of the vehicle on the aerodynamic characteristics of parachute are presented. Numerical simulations are performed using two conservative numerical methods based on the approximation of conservation laws written in integral form for a finite volume. Calculations are based on the parallel algorithms implemented on modern supercomputer systems.
Бабаков В.А. Численное моделирование структуры потока около спускаемого аппарата и расположенного в его следе парашюта при сверхзвуковом движении. Математическое моделирование и численные методы, 2023, № 3, с. 62–79.