Hu, H.; Gao, X.; Gao, Y.; Yang, J. Shock Wave and Aeroelastic Coupling in Overexpanded Nozzle. Preprints2024, 2024031429. https://doi.org/10.20944/preprints202403.1429.v1
APA Style
Hu, H., Gao, X., Gao, Y., & Yang, J. (2024). Shock Wave and Aeroelastic Coupling in Overexpanded Nozzle. Preprints. https://doi.org/10.20944/preprints202403.1429.v1
Chicago/Turabian Style
Hu, H., YuShan Gao and Jianwen Yang. 2024 "Shock Wave and Aeroelastic Coupling in Overexpanded Nozzle" Preprints. https://doi.org/10.20944/preprints202403.1429.v1
Abstract
The increasing demand for higher power in rocket launchers is driving the development of higher power nozzles, achieved essentially by increasing the expansion ratio. However, this can lead to flow separation and resulting unsteady, asymmetrical forces, called side loads, which can limit the life of both the nozzle itself and other engine components. If this problem can be overcome, engine performance can be significantly increased. Therefore, various separation control methods have been proposed, but none have been fully implemented to date due to the uncertainties associated with modeling and predicting the flow phenomena. A numerical study of high area ratio rocket engine is presented to analyze the aeroelastic performance of the structure under the condition of flow separation. The finite volume method, the 2nd order upwind scheme and the extended wall function are used to analyze the flow inside the rocket nozzle and the transition of the Free Shock Separation (FSS) to Restricted Shock Separation (RSS) separation pattern ) to be discussed in detail. Since the location of the flow separation point depends heavily on the flow.
Keywords
shock wave; side load; Aeroelastic; CFD/CSD
Subject
Engineering, Aerospace Engineering
Copyright:
This is an open access article distributed under the Creative Commons Attribution License which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.
