Poststall behavior of a wing under externally imposed sound

被引：20

作者：

Ahmed, NA ^{[1
]}

Archer, RD ^{[1
]}

机构：

[1] Univ New S Wales, Sydney, NSW 2052, Australia

来源：

JOURNAL OF AIRCRAFT | 2001年 / 38卷 / 05期

关键词：

D O I：

10.2514/2.2861

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

The investigation of poststall behavior of a wing was conducted under externally imposed sound. It was observed that acoustic excitation of boundary layer under appropriate frequencies had the potential to provide the extra energy required to modify the severe adverse pressure gradient at or near the stall. The acoustic excitation on a NACA 0012 wing showed suppression of leading-edge separation and improvement in the lift and drag coefficients.

引用

页码：961 / 963

页数：3

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