空军工程大学学报（自然科学版）2016，Vol.17Issue(6)：6-11,6.DOI:10.3969/j.issn.1009-3516.2016.06.002
非对称来流下微型涡流发生器边界层流动控制
A Research on Boundary Layer Control of Asymmetric Supersonic Flow Past Micro Vortex Generator
摘要
Abstract
The supersonic flow (Ma=2.0)past several types of micro�ramps is simulated by the numerical simulation method to improve the characteristics of isolator.The result follows that with the increase of the width at the trailing edge of MVGs,the length of the shock train becomes shorter,and the position of pressure leading edge moves backward.Meanwhile,the spanwise distance of streamwise vortices generated by entirety type MVGs is closer than that of the separated,but the distance to the bottom wall is farther. And the result also indicates that the momentum can be delivered to boundary layer in short distance to im-prove the flow condition.MVGs with wide back width can reduce total pressure skewness and is superior to the basic model.关键词
超声速/隔离段/流动控制/微型涡流发生器/数值仿真Key words
supersonic/isolator/flow control/micro vortex generator/numerical simulation引用本文复制引用
高峰,王旭东,张涵..非对称来流下微型涡流发生器边界层流动控制[J].空军工程大学学报（自然科学版）,2016,17(6):6-11,6.基金项目
航空科学基金(20151396013) （20151396013）
