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

作　　者：高峰[1] 王旭东[1] 张涵[1] 

机构地区：[1]空军工程大学防空反导学院,西安710051

出　　处：《空军工程大学学报（自然科学版）》2016年第6期6-11,共6页Journal of Air Force Engineering University(Natural Science Edition)

基　　金：航空科学基金(20151396013)

摘　　要：为有效改善超燃冲压发动机隔离段性能,运用数值模拟的方法研究了来流马赫数2.0条件下多种结构的微型涡流发生器的流动控制特性。研究结果表明随着微型涡流发生器后缘宽度的增加,隔离段内激波串长度有效缩短,高压前锋后移且整体式略优于分离式;整体式微型涡流发生器产生的流向涡对的横向距离较近,与下壁面的距离较分离式远,能在短距离流动过程中将动量传递给低动量区,有效改善边界层流动性,但作用距离较分离式短;带后缘宽度的微型涡流发生器可有效降低流场总压畸变,对流场质量改善作用要优于基本型。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 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程]