Shock Interaction of a Twin Jet Flow with Side Injection

• Main Authors: Wu, Jheng-Yan, 吳政諺
• Other Authors: Tai, Chang-Hsien
• Format: Others
• Language: zh-TW
• Published: 2017
• Online Access: http://ndltd.ncl.edu.tw/handle/9sye2b

碩士 === 國立屏東科技大學 === 車輛工程系所 === 105 === General fighter tail pipe is basically a single engine and dual engine, and the flowfield with resonant frequency for the twin-engine jet case. While the resonant frequency is the same as the tail structure vibration, it causes damage to structural parts. There are many ways to eliminate the resonance, such as modifying the nozzle shape, side jet and so on. In this paper, the numerical analysis on the effect of side jet flow on the twin jet nozzle flow is studied. In this study, the CFD method was applied to simulate the interaction between the double jet flow and the side jet. The finite volume method is used to solve the Navier-Stokes equation. Firstly, the flowfield between the single nozzle flow with different velocity of side jet flow is observed. Then, to study the shock wave interaction for the twin nozzle flow with different nozzle spacing of the flow field. Finally, the frequency effect of the twin nozzle flow is discussed. The results show that the velocity of the single nozzle is the fastest while the side-to-jet ratio is 0.1, and the position of the shock wave is significantly affected by the different twin nozzle spacing. For the side injetion case, the high frequency fluctuation is disappeared in the twinjet nozzle flowfield.