Impact on the Performance of Micro-Nozzle Straight Exit Section

Jun Jie Tong; Yun Hui Fang

doi:10.4028/www.scientific.net/AMM.635-637.26

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HomeApplied Mechanics and MaterialsApplied Mechanics and Materials Vols. 635-637Impact on the Performance of Micro-Nozzle Straight...

Impact on the Performance of Micro-Nozzle Straight Exit Section

Abstract:

The FLUENT6.3 software is applied to simulate the supersonic flow in micro convergent-divergent nozzle. The simulation is complemented by computing steady 2-D Navier-stokes equations to analyze the pressure contour and velocity contour inside the micro nozzle which has straight exit section or not and the length of straight exit section l. Also the performances of fluent mass coefficients and thrust force efficiencies are studied. The numerical results show: That the nozzle has straight exit section or not and the section length l affect the pressure contour and velocity contour inside the thruster. Compared to the nozzle that has no straight exit section, the minimum pressure region and the maximum velocity region are close to the center of exit in the nozzle that has straight exit section. Also the affected region is increased. When the throat Reynolds number Re is small, the flow coefficient C_d and thrust coefficient η_F firstly increase then decrease with the increase of l.

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Periodical:

Applied Mechanics and Materials (Volumes 635-637)

Pages:

26-30

DOI:

https://doi.org/10.4028/www.scientific.net/AMM.635-637.26

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Cite this paper

Online since:

September 2014

Authors:

Jun Jie Tong, Yun Hui Fang*

Keywords:

Exit Section, Mass Coefficients, Micro Nozzle, Simulation, Thrust Force Efficiencies

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* - Corresponding Author

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