S形进气道流动控制数值模拟研究  

An investigation of secondary flow control in a diffusing S-duct inlet

作　　者：张丽芬[1] 刘振侠[1] 郭东明[1] 王小峰[2] 

机构地区：[1]西北工业大学动力与能源学院,陕西西安710072 [2]中国飞行试验研究院,陕西西安710089

出　　处：《空气动力学学报》2009年第2期240-245,共6页Acta Aerodynamica Sinica

摘　　要：采用CFD技术,结合试飞数据,对某S形进气道进行了加涡流发生器的流动控制数值模拟研究。着重分析了三个不同位置加涡流发生器后,进气道内部二次流的发展;之后比较了不加涡流发生器及不同位置加涡流发生器时进气道出口总压恢复、畸变等情况。结果表明涡流发生器明显地影响着进气道内部二次流的发展变化,涡流发生器对进气道出口周向稳态总压畸变有较大程度改善,但是对于提高总压恢复效果不明显。The objective of this research is to study ways how to reduce distortion at exit of a diffusing S-duct inlet. For this purpose, vortex generators （VGs） were used. Prediction for bare S-duct was compared with flight test to validate the credibility of the numerical method. Reported herein are results for the duct with vortex generators at three different locations. Secondary flow in the three ducts was compared to each other at six cross section, distortion and pressure recovery were also compared. The results show that distortion was improved effectively but pressure recovery was not.

关 键 词：S形进气道 二次流 流动控制 涡流发生器 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]