Research Papers: Fundamental Issues and Canonical Flows

Autogenous Suction to Prevent Laminar Boundary-Layer Separation

[+] Author and Article Information
Hediye Atik

The Scientific and Technical Research Council, Defense Industries Research and Development Institute, PK16 Mamak, Ankara 06261, Turkeyhediye.atik@sage.tubitak.gov.tr

Leon van Dommelen1

Department of Mechanical Engineering, FAMU-FSU College of Engineering, 2525 Pottsdamer Street, Room 229, Tallahassee, FL 32310-6046dommelen@eng.fsu.edu


Corresponding author.

J. Fluids Eng 130(1), 011201 (Dec 19, 2007) (8 pages) doi:10.1115/1.2813135 History: Received February 02, 2006; Revised June 15, 2007; Published December 19, 2007

Boundary-layer separation can be prevented or delayed by sucking part of the boundary layer into the surface, but in a straightforward application the required hydraulics entail significant penalties in terms of weight and cost. By means of computational techniques, this paper explores the possibility of autogenous suction, in which the local pressure differences that lead to separation drive the suction used to prevent it. The chosen examples include steady and unsteady laminar flows around leading edges of thin airfoils. No fundamental theoretical limit to autogenous suction was found in the range of angles of attack that could be studied, but rapidly increasing suction volumes suggest that practical application will become increasingly difficult for more severe adverse pressure gradients.

Copyright © 2008 by American Society of Mechanical Engineers
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Figure 7

Scaled suction coefficient for autogenous suction (circles) and pure suction (squares); ΔCp=0, Ωmin=0.1

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Figure 8

Temporal development of the instantaneous streamlines for a=2 and VwA=0.5 in physical coordinates, but blown-up boundary-layer thickness, at times (a) t=1.0, (b) t=3.0, (c) t=5.0, (d) t=7.0, (e) t=9.0, and (f) ts=10.8

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Figure 9

Streamwise velocity profiles for a=2 at t=5

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Figure 1

Separation control using autogenous suction

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Figure 2

Pressure distribution at scaled angle of attack a=2

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Figure 3

Wall transpiration velocity at successive iterations; a=1.6, ΔCp=0.05, Ωmin=0.1

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Figure 4

Detail of the computational grids near the leading edge in physical coordinates, but blown-up boundary-layer thickness, for a=2 and VwA=0.5 at time t=7. (a) Mesh 1; (b) mesh 3.

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Figure 5

Scaled wall transpiration velocity, wall vorticity (or wall shear), and boundary-layer displacement thickness for various scaled angles of attack a; ΔCp=0.05, Ωmin=0.1

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Figure 6

Wall transpiration velocity for various scaled angles of attack a; ΔCp=0, Ωmin=0.1




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