English (United Kingdom)

https://curated-unify.zendy.io/wp-json/zendy-region/v1/featured_content/oa?rat=en

https://curated-unify.zendy.io/wp-json/zendy-region/v1/highlighted_journal/

Global: Zendy Plus annual

Presents the access of premium content as premium feature

Premium Content

Presents the keyphrase highlighting as premium feature

Keyphrase Highlighting

Presents the summarisation as premium feature

Summarisation

Insights

Presents the pdf analysis as premium feature

PDF Analysis

Presents the zaia usage as premium feature

ZAIA

Global: Zendy Plus monthly

Global: Zendy Tools annual

Global: Zendy Tools monthly

Global: Zendy Free Plan

Solving the reactive low-Mach Navier-Stokes equations with high-orderadaptive methods in time is still a challenging problem, in particular due tothe handling of the algebraic variables involved in the mass constraint. Wefocus on the one-dimensional configuration, where this challenge has longexisted in the combustion community. We consider a model of solid propellantcombustion, which possesses the characteristic difficulties encountered in thehomogeneous or spray combustion cases, with the added complication of an activeinterface. The system obtained after semi-discretisation in space is shown tobe differential-algebraic of index 1. A numerical strategy relying on stifflyaccurate Runge-Kutta methods is introduced, with a specific discretisation ofthe algebraic constraints and time adaptation. High order is shown to bereached on all variables, while handling the constraints properly. Threechallenging test cases are investigated: ignition, limit cycle, and unsteadyresponse with detailed gas-phase kinetics. We show that the time integrationmethod can greatly affect the ability to predict the dynamics of the system.The proposed numerical strategy exhibits high efficiency and accuracy for allcases compared to traditional schemes used in the combustion literature.

High-order adaptive time discretisation of one-dimensional low-Mach reacting flows: a case study of solid propellant combustion