Abstract
A large side load was observed in the supersonic nozzle of the LE-7A rocket engine during startup and shutdown transients. In the present paper, the subscale test and the three-dimensional numerical simulation are carried out to investigate the flow field in the compressed truncated perfect nozzle. The experimental and numerical results show good agreement. The numerical results show that the interaction between the internal shock and the Mach disk cause the cap shock pattern. The separation pattern in the testing nozzle is a free shock separation (FSS). The numerical result predicts the side load does not become large under the FSS condition.
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.
