Abstract
Some aspects of the radiative transfer within and from the exhaust gases of a large rocket engine are discussed. General expressions are given for the radiant flux from nonuniform gases in various limiting cases of large and small opacity at various pressures. Exempletive results of calculations of the equilibrium integrated emission by various infrared bands from the exhaust of a rocket engine operating in a vacuum are given. The work of Montroll and Shuler on the relaxation of a system of harmonic oscillators is extended to include chemical reaction and is used to obtain the total nonequilibrium emission from the fundamental vibration-rotation bands of an optically thin reacting and relaxing gas. The effect of radiative losses on the low-pressure combustion in the turbulent mixing region between two high-velocity parallel streams of reactive gases is discussed in a particular case.
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
