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TECHNICAL PAPERS

Optimal Location of a Synthetic Jet on an Airfoil for Stall Control

[+] Author and Article Information
R. Duvigneau1

Laboratoire de Mécanique des Fluides CNRS UMR6598, Equipe Modélisation Numérique, Ecole Centrale de Nantes, rue de la Noë, 44321 Nantes, FranceRegis.Duvigneau@sophia.inria.fr

A. Hay

Laboratoire de Mécanique des Fluides CNRS UMR6598, Equipe Modélisation Numérique, Ecole Centrale de Nantes, rue de la Noë, 44321 Nantes, Francehay@vt.edu

M. Visonneau

Laboratoire de Mécanique des Fluides CNRS UMR6598, Equipe Modélisation Numérique, Ecole Centrale de Nantes, rue de la Noë, 44321 Nantes, FranceMichel.Visonneau@ec-nantes.fr

1

Corresponding author. INRIA — Projet Opale, 2004 route des lucioles, BP 93, 06902 Sophia-Antipolis, France.

J. Fluids Eng 129(7), 825-833 (Jan 24, 2007) (9 pages) doi:10.1115/1.2742729 History: Received June 06, 2006; Revised January 24, 2007

This study deals with the optimization of the location of a synthetic jet on the suction side of an airfoil to control stall. The optimal location is found by coupling a time-accurate flow solver with adaptive mesh refinement/coarsening techniques and an automatic optimization algorithm. The flow and jet are modeled by the unsteady Reynolds-averaged Navier-Stokes equations (URANSE) with a near-wall low-Reynolds number turbulence closure. An unstructured grid refinement/coarsening method is used to automatically generate meshes adapted to the presence of the synthetic jet at a prescribed location. An optimization algorithm modifies the location of the synthetic jet to determine the best actuator location to increase the time-averaged lift for high angles of attack. The proposed methodology is applied to optimize the location of a synthetic jet on the suction side of the NACA 0012 airfoil at a Reynolds number Re=2×106 and incidences of 18deg and 20deg. Finally, a physical analysis of the influence of the synthetic jet location on the control efficiency is proposed to provide some guidelines for practical jet positioning.

Copyright © 2007 by American Society of Mechanical Engineers
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References

Figures

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Figure 1

Configuration of the computations

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Figure 2

Relationship between the different generations of elements

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Figure 3

Refinement of two-dimensional volumes

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Figure 5

Successive refined grid

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Figure 6

Grid refinement study

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Figure 7

Streamlines without actuation

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Figure 8

Lift coefficient with respect to the angle of attack

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Figure 9

Lift coefficient with respect to the jet position

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Figure 10

Lift coefficient history for incidence 18deg

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Figure 11

Lift coefficient history for incidence 20deg

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Figure 12

Pressure coefficient at the maximum lift time for incidence 18deg

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Figure 13

Pressure coefficient at the minimum lift time for incidence 18deg

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Figure 14

Pressure coefficient at the maximum lift time for incidence 20deg

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Figure 15

Pressure coefficient at the minimum lift time for incidence 20deg

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Figure 16

Incidence 18deg, s=0.1l

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Figure 17

Incidence 18deg, s=sopt18

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Figure 18

Incidence 18deg, s=0.3l

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Figure 19

Incidence 20deg, s=0.1l

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Figure 20

Incidence 20deg, s=sopt20

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Figure 21

Incidence 20deg, s=0.2l

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