High order finite volume schemes with IMEX time stepping for the Boltzmann model on unstructured meshes

TL;DR

This paper develops high-order finite volume schemes with IMEX time stepping for solving the full Boltzmann equation on unstructured meshes, combining spectral and CWENO techniques for efficiency and accuracy.

Contribution

It introduces a novel combination of CWENO reconstruction with IMEX schemes for the Boltzmann equation on unstructured meshes, enhancing stability and computational efficiency.

Findings

Achieves high-order accuracy in space and time.

Demonstrates stability and asymptotic preservation.

Validates methods on benchmark and engineering problems.

Abstract

In this work, we present a family of time and space high order finite volume schemes for the solution of the full Boltzmann equation. The velocity space is approximated by using a discrete ordinate approach while the collisional integral is solved by spectral methods. The space reconstruction is realized by integrating the distribution function, describing the state of the system, over arbitrary shaped and closed control volumes using a Central Weighted ENO (CWENO) technique. Compared to other reconstruction methods, this approach permits to keep compact stencil sizes which is a remarkable property in the context of kinetic equations due to the considerable demand of computational resources. The full discretization is then obtained by combining the previous phase-space approximation with high order Implicit-Explicit (IMEX) Runge Kutta schemes. These methods guarantee stability, accuracy and preservation of the asymptotic state. Comparisons of the Boltzmann model with simpler relaxation type kinetic models (like BGK) is proposed showing the capability of the Boltzmann equation to capture different physical solutions. The theoretical order of convergence is numerically measured in different regimes and the methods are tested on several standard two-dimensional benchmark problems in comparison with Direct Simulation Monte Carlo results. The article ends with a prototype engineering problem consisting of a subsonic and a supersonic flow around a NACA 0012 airfoil. All test cases are run with MPI parallelization on several threads, thus making the proposed methods suitable for parallel distributed memory supercomputers.