超声速气流中横向气体射流混合经验模型  

Empirical mixing model of transverse gaseous jet in supersonic flow

作　　者：杨揖心 王振国[1] 孙明波[1] 汪洪波[1] 

机构地区：[1]国防科学技术大学航天科学与工程学院,长沙410073

出　　处：《航空动力学报》2015年第6期1391-1399,共9页Journal of Aerospace Power

基　　金：霍英东教育基金高等院校青年教师基金(131055)

摘　　要：为了获得适用于工程估算的射流穿透经验关系式,对射流中心迹线、穿透边界及喷注物展向分布特性进行模化处理,建立了描述超声速气流中横向气体射流混合经验模型,并通过系列实验观测结果对该模型有效性进行验证.结果表明：在较宽的动量比范围内（动量比为0.5~5.3）,该模型预测的射流中心迹线和穿透边界均与实验图像吻合较好,在射流中心迹线附近,该模型预测的喷注物摩尔分数与实验测量值相比误差在5%以内,精度优于现有模型.随着动量比的增大,在喷孔下游一定区域内,射流引起的反转旋涡对增强,导致该模型对展向摩尔分数分布的预估产生一定误差,表明该模型的适用范围与动量比和下游距离等因素相关.In order to obtain empirical correlations of jet penetration for engineering application,a empirical mixing model for the analysis of transverse gaseous jet in supersonic flow was investigated by modeling the jet centerline,penetration boundary and injection’s spanwise distributional characteristics.Several experimental cases were used to verify the performance of the present model.Results indicate that,within the momentum flux ratio of0.5-5.3,the present model agreed well with the experiment image both in the jet centerline and penetration boundary,and in the area near jet centerline,the model predicted a injection mole fraction with an error less than 5%,which shows a higher precision in contrast with the existing models.With the increasing of the momentum flux ratio,the counter-rotating vortex pairs are strengthened in the near region downstream of the injector,which leads to some inaccuracy of spanwise mole fraction distribution calculated by the present model.This indicates that the present model validity is affected by the momentum flux ratio and downstream distance.

关 键 词：超声速气流 横向射流 混合模型 射流中心迹线 穿透边界 动量比 

分 类 号：V411.1[航空宇航科学与技术—航空宇航推进理论与工程]