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Passive control of dynamic stall using a flow-driven micro-cavity actuator

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Abstract

A novel passive flow control strategy for the mitigation of transient separation and dynamic stall is demonstrated by means of high-fidelity large-eddy simulations. The control technique is based on a properly-sized micro-cavity cut into a wing’s underside near the leading edge, ahead of stagnation. This cavity remains essentially inactive at low incidence. However, as the wing effective angle of attack increases, the stagnation point displaces past the micro-cavity and the accelerating flow grazing the cavity induces a high-frequency resonance phenomenon or so-called Rossiter modes. The self-generated small-scale disturbances are carried around the leading-edge through the boundary layer to the wing’s upper side where the laminar separation bubble (LSB) amplifies these disturbances. This process delays LSB bursting and dynamic stall when the cavity size is selected such that its naturally occurring Rossiter modes are tuned to the receptivity of the LSB. Control effectiveness is explored for a harmonically pitching NACA 0012 wing section with freestream Mach number \(M_\infty = 0.2\), chord Reynolds numbers \(\textrm{Re}_\textrm{c} = 5 \times 10^5\), and maximum angle of attack of \(18^\circ \). The flow fields are computed employing a validated overset high-order implicit large-eddy simulation (LES) solver based on sixth-order compact schemes for the spatial derivatives augmented with an eighth-order low-pass filter. Despite its simplicity, the micro-cavity resonance is found to be highly effective in preventing the deep dynamic stall experienced by the baseline airfoil. A significant reduction in the cycle-averaged drag and in the force and moment fluctuations is achieved. In addition, the negative (unstable) net-cycle pitch damping found in the baseline cases is eliminated.

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Abbreviations

c :

Airfoil chord

\(C_\textrm{L}, C_\textrm{D}, C_\textrm{M}\) :

Lift, drag and quarter-chord moment coefficients

\(C_\textrm{p}\) :

Pressure coefficient

D :

Micro-cavity depth

DSV:

Dynamic stall vortex

k :

Reduced frequency, \(\pi f c / U_\infty \)

L :

Micro-cavity length

LSB:

Laminar separation bubble

m :

Micro-cavity resonance modes

M :

Mach number

\(\textrm{Re}_\textrm{c}\) :

Reynolds number based on chord, \(\rho _{\infty } U_{\infty } c / \mu _{\infty }\)

s :

Span width for spanwise-periodic computations

SLV:

Shear-layer vortex

St :

Non-dimensional frequency, \(fc/U_\infty \)

t :

Time

u, v, w :

Cartesian velocity components

\(U_\infty \) :

Freestream velocity

x, y, z :

Cartesian coordinates

\(\alpha \) :

Angle of attack

\(\Delta t\) :

Time step size

\(\mu \) :

Molecular viscosity coefficient

\(\xi ,\eta ,\zeta \) :

Body-fitted computational coordinates

\(\zeta _\textrm{d}\) :

Net-cycle pitch damping

\(\rho \) :

Fluid density

\(\omega _x, \omega _y, \omega _z\) :

Vorticity components

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Funding

This work was supported in part by AFOSR under task LRIR 20RQCOR053 monitored by Dr. G. Abate and by a grant of HPC time from the DoD HPC Shared Resource Centers at AFRL and ERDC.

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Authors and Affiliations

  1. Air Force Research Laboratory, Wright-Patterson AFB, OH, 45433, USA

    Miguel R. Visbal & Daniel J. Garmann

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  1. Miguel R. Visbal
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  2. Daniel J. Garmann
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Correspondence to Miguel R. Visbal.

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The data sets generated during the current study are available from the authors upon reasonable request.

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The authors declare no competing financial interests.

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Both authors contributed equally to this project.

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Communicated by Vassilis Theofilis.

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Visbal, M.R., Garmann, D.J. Passive control of dynamic stall using a flow-driven micro-cavity actuator. Theor. Comput. Fluid Dyn. 37, 289–303 (2023). https://doi.org/10.1007/s00162-023-00645-2

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