Flows in Complex Systems

Parametric Study of Dynamic Stall Flow Field With Synthetic Jet Actuation

[+] Author and Article Information
Joshua Yen1

Noor A. Ahmed

School of Mechanical and Manufacturing Engineering,  University of New South Wales, Sydney, NSW, 2052, Australia


Corresponding author.

J. Fluids Eng 134(7), 071106 (Jun 25, 2012) (8 pages) doi:10.1115/1.4006957 History: Received September 28, 2011; Revised May 31, 2012; Published June 25, 2012; Online June 25, 2012

A parametric study of the interaction between dynamic stall and a zero-net mass flux synthetic jet installed on a wing was investigated by identifying the dominant frequencies in the resulting flow field using spectral analysis. The instantaneous pressure distribution around an NACA 0020 wing was recorded by performing static and dynamic experiments using an open jet subsonic wind tunnel located at the aerodynamics laboratory of the University of New South Wales. The results obtained provided valuable insight into the interaction process. The oscillation frequency and its harmonics were identified in baseline dynamic experiments, as well as the jet frequency and offset frequencies with synthetic jet actuation. The offset frequencies, similar to beat frequencies, were found to be a dynamic effect and represented the complex and nonlinear interaction between dynamic stall and the synthetic jet. The study suggests that low amplitude synthetic jet actuation would be an effective method in enhancing the overall aerodynamic efficiency of the wing. This confirmed the viability of utilizing synthetic jets in dynamic stall control.

Copyright © 2012 by American Society of Mechanical Engineers
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Figure 1

Pressure tapping locations (top) and synthetic jet slot and plenum chamber (bottom)

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Figure 2

Schematic diagram of experimental rig

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Figure 3

Collapse of pressure domain at Reynolds number of 2.5 × 105 from 15 deg to 16 deg without synthetic jet actuation

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Figure 4

Static stall angle for Reynolds number between 1.3 × 105 and 2.5 × 105 in NC (triangles) and SJ (circles) experiments

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Figure 5

PSD plot at 14 deg (top) and 17 deg (bottom) at x/c = 0.27 (left) and x/c = 0.60 (right)

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Figure 6

Normal (top) and chord (bottom) coefficient hysteresis loops at κ = 0.16

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Figure 7

NC temporal evolution of pressure distribution at κ = 0.16

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Figure 8

SJ temporal evolution of pressure distribution at κ = 0.16

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Figure 9

Pressure coefficient PSD plots at κ = 0.16 at x/c = 0.27 (top left), 0.40 (top right), 0.60 (bottom left), and 0.82 (bottom right)

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Figure 10

Pressure coefficient PSD plots at x/c = 0.40 at κ = 0.1 (top left), 0.11 (top right), 0.16 (bottom left), and 0.21 (bottom right)

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Figure 11

Pressure coefficient PSD plot with no actuation, Cμ = 4.6 × 10-6 and Cμ = 1.1 × 10-3 for κ = 0.16 at x/c=0.27 (top) and 0.60 (bottom)

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Figure 12

Normal force PSD plots at κ = 0.1 (top) and 0.24 (bottom)

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Figure 13

Chord force PSD plots at κ = 0.1 (top) and 0.24 (bottom)



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