基于双流体模型的超声速两相横向喷射流场研究

李东霞; 徐旭; 蔡国飙

基于双流体模型的超声速两相横向喷射流场研究

北京航空航天大学宇航学院, 北京 100083

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出版历程
- 收稿日期: 2007-03-27
- 修回日期: 2007-06-01
- 刊出日期: 2007-10-28

Investigation of two-phase flow in supersonic crossflow based on two-fluid method

School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

摘要

摘要: 对两相超声速横向喷射试验进行了数值模拟.采用双流体两相流模型,在不同直径液滴和不同动压比条件下分别对两相超声速横向喷射流场进行了计算.结果表明:雾化液滴直径和喷射动压比对液体的横向穿透深度影响很大;雾化液滴直径的大小或者动压比的大小对喷口下游流场的影响区域是不同的.数值模拟结果与试验结果符合良好,为进一步的研究打下良好基础.
- 航空、航天推进系统 /
- 两相流 /
- 双流体 /
- 超声速 /
- 喷射
Abstract: Two-fluid model was employed to simulate two-phase phenomena of supersonic crossflow.Calculations were carried out under different diameter droplets and different momentum flux ratio conditions respectively to examine how they affected flow field.Numerical simulation results show that the cross-stream penetration of the jet is influenced evidently by the droplets diameter and momentum flux ratio;and the downstream flow of the muzzle changes when the droplet diameter or momentum flux ratio varies.The calculation results agree well with experimental results.
- aerospace propulsion system /
- two-phase flow /
- two-fluid method /
- supersonic /
- jet

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参考文献(7)

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