Abstract
A thermal‐hydraulic model of an open‐cycle gas core nuclear rocket is developed. The two‐dimensional Navier‐Stokes equations, the energy equation, and the species diffusion equation are solved for high temperature two‐species gas flow. A description of the model and the method of solution is presented, as well as the results for a cylindrical gas core reactor design. The results provide valuable insight into the fluid flow and species mixing within an open‐cycle gas core nuclear rocket.
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.
