Drag reduction due to riblets on a GAW(2) airfoil

被引：12

作者：

Subaschandar, N ^{[1
]}

Kumar, R ^{[1
]}

Sundaram, S ^{[1
]}

机构：

[1] Natl Aerosp Labs, Expt Aerodynam Div, Bangalore 560017, Karnataka, India

来源：

JOURNAL OF AIRCRAFT | 1999年 / 36卷 / 05期

关键词：

D O I：

10.2514/2.2524

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

An attempt to assess the total drag reduction that is due to riblets on a cambered airfoil up to high angles of attack at low speeds is presented. The 13% thickness general aviation wing [GAW(2)] airfoil section was chosen because of its strong relevance in many applications. The increased effectiveness of riblets in adverse pressure gradients up to a certain value of β, beyond which the effectiveness is reduced is demonstrated, presumably because of the strong deceleration of the boundary layer, which leads to separation on the airfoil upper surface.

引用

页码：890 / 892

页数：3

共 11 条

[1] RESUME OF IMPORTANT RESULTS PRESENTED AT THE 3RD TURBULENT DRAG REDUCTION WORKING PARTY
COUSTOLS, E
SAVILL, AM
[J]. APPLIED SCIENTIFIC RESEARCH, 1989, 46 (03): : 183 - 196
[2] COUSTOLS E, 1992, AGARD786 FDP VKI
[3] DESAI SS, 1982, 891982 RHUR U
[4] DUTT HNV, 1987, AE8701 TM NAT AER LA
[5] DUTT HNV, 1989, AIAA J, V7, P658
[6] Kline S.J., 1952, ASME Mechanical Engineering, V75, P3, DOI DOI 10.1016/J.CHAOS.2005.11.046
[7] SCHLICHTING H, 1979, BOUNDARY LAYER THEOR, P711
[8] SUBASCHANDAR N, 1995, EA9504 PD NAT AER LA
[9] Viscous drag reduction using riblets on NACA 0012 airfoil to moderate incidence
Sundaram, S
Viswanath, PR
Rudrakumar, S
[J]. AIAA JOURNAL, 1996, 34 (04) : 676 - 682
[10] TURBULENT DRAG REDUCTION USING RIBLETS ON A SUPERCRITICAL AIRFOIL AT TRANSONIC SPEEDS
VISWANATH, PR
MUKUND, R
[J]. AIAA JOURNAL, 1995, 33 (05) : 945 - 947

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