超声速气流中横向射流雾化实验和数值模拟

刘静; 王辽; 张佳; 韦宝禧; 徐旭

超声速气流中横向射流雾化实验和数值模拟

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: 2007-04-03
- 修回日期: 2007-06-11
- 刊出日期: 2008-04-28

Experimental and numerical simulation of atomization of liquid jet in supersonic crossflow

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

摘要

摘要: 为了对超声速气流中的横向射流雾化过程进行研究,在直连式实验台上进行了超声速气流中的横向射流雾化实验,并对实验工况进行了数值模拟.超声速来流的马赫数为2,实验喷雾的动压比范围为1.～11.7,实验工质为水.采用纹影法对射流雾化过程进行了拍摄,得到了有雾化的超声速流场结构和穿透深度拟合公式.同时采用欧拉-拉格朗日两相流计算方法对实验工况进行了数值模拟,雾化模型采用了一种新型K-H(Kelvin-Helmholtz)和R-T(Rayleigh-Taylor)混合模型,数值模拟与实验结果符合较好.
- 航空、航天推进系统 /
- 超声速 /
- 雾化 /
- 实验 /
- 数值模拟 /
- 两相流
Abstract: The liquid jet atomization in supersonic crossflow was investigated experimentally in a supersonic wind tunnel and the present experiment was numerically simulated.The Mach number of the supersonic flow was 2 and dynamic pressure ratio varied from 1.6 to 11.7,and water was used as test liquid.Schlieren method was used to study the structure of liquid jet in supersonic flow field and the correlation for penetration height was developed.Numerical simulation used EulerianLagrangian method to describe the two-phase flow.Anew hybrid K-H(Kelvin-Helmholtz) and R-T(Rayleigh-Taylor) atomization model was used to describe the atomization process.
- aerospace propulsion system /
- supersonic /
- atomization /
- experiment /
- numerical simulation /
- two-phase flow

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参考文献(15)

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