CFD Analysis of Aircraft Curved C-D Nozzle: Technical Note

• Published in: International journal of vehicle structures and systems Vol. 11; no. 3
• Main Authors: Sivaganesan, S., Ferdaus, F., Dhanasekaran, C., Sathishkumar, G., Sivabalan, S.
• Format: Journal Article
• Language: English
• Published: 03.12.2019
• ISSN: 0975-3060; 0975-3540
• DOI: 10.4273/ijvss.11.3.07

A nozzle for the aircraft can be designed by considering the exit Mach number. In order to get a premeditated Mach number, we need to convert pressure energy into kinetic energy by using a nozzle. Convergent nozzles are utilized for subsonic flows while Convergent-Divergent (C-D) nozzle is utilized for supersonic flows. Curved nozzle flow is accelerated from low subsonic to sonic velocity at the throat and further expanded to supersonic velocities at the exit, in a C-D nozzle. This paper details the relevancies on designing a curved nozzle to attain super-sonic flow and maximizing the optimal thrust and devoid of flow separation due to shock waves. The navigation of the flow must be parallel to the axis of the nozzle for achieving extreme thrust and proficiency. Based on the fundamental gas dynamic equations, this study aims to develop a theoretical approach for the calculation of the flow properties along the axis of the C-D Nozzle. The flow conditions were selected in consideration of the pressure, temperature and gases accessible at the exit of the combustion chamber.