基于POD方法的高超声速边界层转捩判定方法  

Transition Method in Hypersonic Boundary Layer Based on POD Method

作　　者：魏斌斌[1] 高永卫[1] 邓磊[1] 赵学军[2] 

机构地区：[1]西北工业大学翼型研究中心,陕西西安710072 [2]中国航天空气动力技术研究院,北京100074

出　　处：《气体物理》2016年第3期25-30,共6页Physics of Gases

基　　金：中国航天科技集团公司航天科技创新基金(0100-N2014KC0046)

摘　　要：高超声速边界层转捩是高超声速飞行器设计的关键基础问题之一.为了研究高超声速边界层转捩,在风洞中,对平板模型进行了M=5的实验,在模型中心沿流动方向使用PCB脉动压力传感器对脉动压力时间序列进行采集.文章将本征正交分解(proper orthogonal decomposition,POD)方法引入高超声速脉动压力数据处理中,发展了单点POD分析方法.经验证,使用该方法重构数据的均方根(root mean square,RMS)峰值位置可表征转捩位置,实用性强.Hypersonic boundary layer transition is one of the key basic problems. To study the hypersonic boundary layer transition,an experiment at M = 5 with a flat plate model was conducted. PCB dynamic pressure sensors were used along flow direction in the center of model to acquire fluctuating pressure time series. POD（ proper orthogonal decomposition） analysis method was introduced to hypersonic fluctuating pressure data processing,and the single point of POD analysis method was developed. It is proved that the peak position of root mean square value of the fluctuating pressure data reconstructed by this method which has strong adaptability can characterize the transition position.

关 键 词：高超声速边界层转捩 脉动压力 单点POD分析方法 第2模态 

分 类 号：O357.4[理学—流体力学]