What is it about?
Methane is a promising propellant for future reusable liquid rocket engines. The use of hydrocarbon fuel requires to revisit the numerical tools for the simulation of rocket combustion chambers. We investigate models of varying fidelity and efficiency for LES of oxygen-methane combustion using a 7-element subscale test case. The simulation results are compared to experimental data.
Featured Image
Read the Original
This page is a summary of: Assessment of Presumed/Transported Probability Density Function Methods for Rocket Combustion Simulations, Journal of Propulsion and Power, July 2019, American Institute of Aeronautics and Astronautics (AIAA),
DOI: 10.2514/1.b37331.
You can read the full text:
Contributors
Be the first to contribute to this page
