湍流减阻新概念的实验探索  

The Experimental Approach to Drag Reduction of the Transverse Ribbons on Turbulent Flow

作　　者：潘家正[1] 

机构地区：[1]南京航空航天大学

出　　处：《空气动力学学报》1996年第3期304-310,共7页Acta Aerodynamica Sinica

摘　　要：本文对当今湍流表面摩擦减阻新概念进行了初步的风洞实验探索。将垂直于流动方向的小尺寸肋条按一定的间隔距离固定在平板上，利用自制的悬挂式天平测量了不同风速时的阻力，获得了约１０．２％的减阻效果。实验中分别考察了肋条参数对减阻的影响，使用Ｘ型热线风速仪研究了雷诺应力的型态。从湍流边界层涡结构的观点出发，提出了边界层底部“微型空气轴承（ＭＡＢＳ）”减阻新概念以及涡结构干扰对减阻的影响，并认为平均速度型态的改善是湍流表面摩阻减小的结果，雷诺应力型态的改善将是湍流减阻的基本研究内容之一。This paper gives the experimental approach primarily in wind tunnel to the new concept of surface drag reduction on turbulent flow.The effeciency about 10 .2 percent has been gotten when the drag is measured under different velocities using the drag balance made by the author, mounting a series of small size ribbons transverse streamwise arranged in a fixed space. The experiment investigates the effects of ribbon parameters on drag reduction, and the research of Reynolds stress profiles is made using the X-configuration hot-wire anemometer. As viewed from vortice structure of turbulent boundary layer, the new concept of drag reduction beneath the boundary layer 'Micro-Air Bearings' and the effect of interfered vortice structure on drag reduction are proposed, and it is suggested that the improvement of the average velocity profile results from the turbulent surface friction reduction and the improvement of the Reynolds stress profile is considered as one of the basic research on turbulent drag reduction.

关 键 词：湍流边界层 摩擦减阻 风洞试验 雷诺应力 

分 类 号：V211.19[航空宇航科学与技术—航空宇航推进理论与工程]