@inproceedings{7483cf21195943d1bc1bab78671fa743,
title = "Supersonic combustion of cavity flow; a computational approach using les",
abstract = "The effect of Mach number on the combustion processes and instabilities is computationally studied for a range of Mach numbers M∞ =1.5 ÷ 3.0. The computations are carried out suing the large-eddy simulation (LES) approach. The analysis reveals the presence of a region of high level of temperature, NO and CO2 inside the cavity. The reverse 2 flow causes a preferential distribution of this region towards the step side of the cavity.",
author = "Marcel Ilie and Augustin Semenescu and Geoffrey Sullivan",
note = "Publisher Copyright: {\textcopyright} 2021, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.; AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2021 ; Conference date: 11-01-2021 Through 15-01-2021",
year = "2021",
doi = "10.2514/6.2021-1572",
language = "English",
isbn = "9781624106095",
series = "AIAA Scitech 2021 Forum",
publisher = "American Institute of Aeronautics and Astronautics Inc, AIAA",
pages = "1--7",
booktitle = "AIAA Scitech 2021 Forum",
}