超声速气流中横向射流雾化实验和数值模拟  

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

作　　者：刘静[1] 王辽[1] 张佳[1] 韦宝禧[1] 徐旭[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100083

出　　处：《航空动力学报》2008年第4期724-729,共6页Journal of Aerospace Power

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1．6～11．7，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．同时采用欧拉一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．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 Eulerian-Lagrangian method to describe the two-phase flow. A new hybrid K-H（Kelvin-Helmholtz） and R-T（Rayleigh-Taylor） atomization model was used to describe the atomization process.

关 键 词：航空、航天推进系统 超声速 雾化 实验 数值模拟 两相流 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]