涡流发生器研制及其对边界层的影响研究  

Development of the Vortex-Generator and Study on the Effect of Vortex-Generator on Boundary Layer

作　　者：倪亚琴[1] 

机构地区：[1]中国空气动力研究与发展中心

出　　处：《空气动力学学报》1995年第1期110-116,共7页Acta Aerodynamica Sinica

摘　　要：本文主要介绍了涡流发生器的机理和用途，涡流发生器研制和使用的一些重要参数，并进行了分析和验证。通过风洞试验段侧壁边界层和马赫数分布测量及半模型试验，证明该涡流发生器的研制是成功的。在风洞试验段侧壁安装涡流发生器情况下，在马赫数０．４至０．９范围，使涡流发生器下游８８０ｍｍ处侧壁上的边界层约减薄了７１％，而且对流场均匀度没有影响，并使半模试验有所改善。The paper presents the mechanism and application of vor-tex-generator,the development of a vortex-generator, as well as some important parameters used.The analysis and the verification of vortex-generator have been given. From the measured boundary layer thickness and distribution of Mach number along side wall of the test section of wind tunnel,it has been shown that the present vortex-generator is a suc-cessful desig.With the vortex-generator,the boundary layer thickness can be decreased about 71%atM=0.4～0.9 at the place 880mm down stream of the vortex-generator and it has no influence on the main flow while the test results of half model is improved.

关 键 词：涡流发生器 边界层 半模型试验 气流分离 机翼 

分 类 号：V224.4[航空宇航科学与技术—飞行器设计]