Aerothermodynamic Analysis of a Radiation Cooled Blunt Re-Entry Vehicle Over a Ballistic Trajectory Itle
Aim of this paper is to model and numerically simulate the aerothermodynamics phenomena for non-ablative radiation cooled hypersonic re-entry vehicles. The simulation specifically solves for a nominal geometry using current surface materials of a blunt shape non-winged re-entry vehicle entering atmosphere on a ballistic trajectory. Computational fluid dynamics (CFD) is used to obtain flow field that develops around a re-entry capsules. Re-entry problem is of particular interest since it features most aspects of the hypersonic flow around a re-entry vehicle. A high-speed flow generates bow shock wave over a re-entry vehicle which causes high surface pressure and high aerodynamic drag required for aero-braking purposes. Determination of the exact location and shape of shock wave and the extension of the recirculation zone is particularly a challenging task for numerical simulation.Flow computations have been carried out using a density based solver, with free stream condition at two different Mach numbers on a ballistic trajectory. Model and mesh are created in ICEM CFD® 14.5 and FLUENT® 14.5 is used for simulation. Real gas effects are taken into account. The computational analysis of re-entry bodies involving heat loads, temperatures, velocities, Mach numbers and pressures at various locations of the capsules are presented.
Authors: Asim Shahzad, and Ali Sarosh
Conference: SAMPE Seattle 2017