Influence of trailing-edge flow control on airfoil performance

被引：27

作者：

Gai, SL ^{[1
]}

Palfrey, R ^{[1
]}

机构：

[1] Australian Def Force Acad, Canberra, ACT 2600, Australia

来源：

JOURNAL OF AIRCRAFT | 2003年 / 40卷 / 02期

关键词：

D O I：

10.2514/2.3097

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

Experiments were conducted on a NACA 0012 airfoil equipped with Gurney flap. Two types of Gurney flap were used: one was solid with a height of 5% chord and the other was triangularly serrated with a height of 5% chord. The Reynolds number of the tests, similar to2 X 10(5) based on chord, was typically in the range of interest for microaerial vehicles and rotor blades of helicopters. The results confirmed the advantages of a Gurney flap, in general, and provided additional insight into their effectiveness. A simple analysis that extends the hypothesis of Liebeck on the functioning of the Gurney flap is offered.

引用

页码：332 / 337

页数：6

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