Deployable Vortex Generator Dynamic Stall Alleviation through Experimental and Numerical Investigations

被引：4

作者：

Joubert, G. ^{[1
]}

Le Pape, A. ^{[1
]}

Heine, B. ^{[2
]}

Huberson, S. ^{[3
]}

机构：

[1] ONERA French Aerosp Lab, Appl Aerodynam Dept, Meudon, France

[2] German Aerosp Ctr DLR, Inst Aerodynam & Flow Technol, Gottingen, Germany

[3] Univ Poitiers, CNRS, Inst P, Poitiers, France

来源：

JOURNAL OF THE AMERICAN HELICOPTER SOCIETY | 2013年 / 58卷 / 03期

关键词：

TURBULENCE; AIRFOILS; FLOW;

D O I：

10.4050/JAHS.58.032005

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

The flow over an OA209 airfoil subjected to a sinusoidal pitching motion under dynamic stall conditions and equipped with an innovative deployable vortex generator actuator inducing stall control is experimentally and numerically investigated. Pressure and time-resolved particle image velocimetry measurements allow a detailed comparison to be performed between clean and controlled cases, including separation point detection and proper orthogonal decomposition analysis. Along with wind tunnel testing, numerical simulations are performed by solving the unsteady Reynolds-averaged Navier-Stokes equations with the ONERA elsA code. Computations are successfully compared to the experimental reference and bring further understanding of the deployable vortex generator actuation.

引用

页数：13

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