On the calculation of the electron temperature flowfield in the DSMC studies of ionized re-entry flows

Alexander Shevyrin,Yevgeniy Bondar

doi:10.1186/s42774-020-00031-0

Abstract

Currently available procedures of electron temperature calculations in studying ionized flows around reentry spacecraft by the direct simulation Monte Carlo (DSMC) method are analyzed. It is shown that the heat conduction of electrons is not taken into account in these procedures. The contributions of various effects to the electron energy balance are calculated by an example of the RAM-C II capsule, and a numerical solution of the electron energy conservation equation is obtained, which refines the electron temperature distribution used in the DSMC computations. A method of coupled calculation of the electron temperature within the framework of the continuum approach and modelling of ionized gas flow by the DSMC method is proposed.

Highlights

1 Introduction The direct simulation Monte Carlo (DSMC) method [1] is traditionally used for studying high-altitude aerothermodynamics of space vehicles
The study of the plasma surrounding the reentry vehicle is of significant interest, and effective models that can be used in DSMC computations have to be developed for investigating high-altitude aerothermodynamics of prospective space vehicles [2]
5 Conclusions A method of a detailed analysis of energy balance for the electron component in weakly ionized high-enthalpy air flows around space vehicles entering the Earth atmosphere has been proposed

Summary

Introduction

The direct simulation Monte Carlo (DSMC) method [1] is traditionally used for studying high-altitude aerothermodynamics of space vehicles. A shock layer is formed around a space vehicle entering the atmosphere with a high velocity. At high velocities of atmospheric reentry (more than 10 km/s), when the ionization degree becomes rather high, ionization affects both the gas flow around the Shevyrin and Bondar Advances in Aerodynamics (2020) 2:6 space vehicle and the convective heat flux onto the vehicle surface. The study of the plasma surrounding the reentry vehicle is of significant interest, and effective models that can be used in DSMC computations have to be developed for investigating high-altitude aerothermodynamics of prospective space vehicles [2]

Objectives

Methods

Results

Conclusion