Numerical Modelling of Hypersonic Flow of Spacecrafts

Abstract

Numerical simulations of rarefied gas flows are an important area in the design of aerospace vehicles. They can provide a suitable alternative to experiments, which can be often too complicated due to extreme conditions. Navier-Stokes equations, which describe continuum fluid flow, generally lose their applicability in low pressures. As a result, it is necessary to adjust these equations or use alternative models. This article studies the possibility of using a continuum numerical model for a simulation of a hypersonic flow of a reentry module. Based on the Knudsen number, it was shown that it is still possible to use Navier-Stokes equations either without any adjustments or with the addition of a slip flow boundary condition.