High-order spatial discretizations significantly improve the accuracy of flow simulations. In this work, a multi-dimensional limiting process with low diffusion (MLP\documentclass[12pt]{minimal} \usepackage{amsmath} \usepackage{wasysym} \usepackage{amsfonts} \usepackage{amssymb} \usepackage{amsbsy} \usepackage{mathrsfs} \usepackage{upgreek} \setlength{\oddsidemargin}{-69pt} \begin{document}$$^\text {ld}$$\end{document}) and up to fifth order accuracy is employed. The advantage of MLP is that all surrounding volumes of a specific volume may be used to obtain cell interface values. This prevents oscillations at oblique discontinuities and improves convergence. This numerical scheme is utilized to investigate three different rocket combustors, namely a seven injector methane/oxygen combustion chamber, the widely simulated PennState preburner combustor and a single injector chamber called BKC, where pressure oscillations are important.
Rocket Combustion Chamber Simulations Using High-Order Methods
Notes Numerical Fluid Mech.
Future Space-Transport-System Components under High Thermal and Mechanical Loads ; Chapter : 24 ; 381-394
2020-10-27
14 pages
Article/Chapter (Book)
Electronic Resource
English
Rocket Combustion Chamber Coating
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