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Investigation of three-dimensional dynamic stall on an airfoil using fast-response pressure-sensitive paint

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Abstract

Dynamic stall on a pitching OA209 airfoil in a wind tunnel is investigated at Mach 0.3 and 0.5 using high-speed pressure-sensitive paint (PSP) and pressure measurements. At Mach 0.3, the dynamic stall vortex was observed to propagate faster at the airfoil midline than at the wind-tunnel wall, resulting in a “bowed” vortex shape. At Mach 0.5, shock-induced stall was observed, with initial separation under the shock foot and subsequent expansion of the separated region upstream, downstream and along the breadth of the airfoil. No dynamic stall vortex could be observed at Mach 0.5. The investigation of flow control by blowing showed the potential advantages of PSP over pressure transducers for a complex three-dimensional flow.

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Abbreviations

\(A_{\rm Ref}\) :

Reference area for \(C_{\rm L}, C_{\rm D}, C_{\rm M} \; (=0.3\,\hbox {m}^2)\)

\(\alpha \) :

Angle of attack (\(^\circ \))

\(\beta \) :

Vortex rotation angle (\(^\circ \))

\(b\) :

Airfoil model breadth (\(b=0.997\) m)

\(c\) :

Airfoil model (\(c=0.300\) m)

\(C_{\rm L}\) :

Lift coefficient

\(C_{\rm M}\) :

Pitching moment coefficient

\(C_{\rm P}\) :

Pressure coefficient

\(C_{\rm P-crit}\) :

Critical pressure coefficient

\(C_{{\rm P}_0}\) :

\(C_{\rm P}\) at minimum angle of attack

\(C_{\mu }\) :

Momentum ratio jets/freestream: \(C_{\mu }=\frac{2}{cL_{\rm act}}\frac{\dot{m}_{\rm m}v_{\rm j}}{\rho _{\infty }v^2_{\infty }}\)

\(f\) :

Frequency (Hz)

\(k\) :

Reduced frequency: \(k=\pi fc/v_{\infty }\)

\(L_{\rm act}\) :

Breadth of model with actuation (m)

\(M\) :

Mach number

\(\dot{m}_{\rm m}\) :

Mass flux for the model (kg/s)

\(Re\) :

Reynolds number based on \(c\)

\(\rho _{\infty }\) :

Freestream flow density (\(\hbox {kg/m}^3\))

\(s\) :

Jet spacing in \(y\)-direction (m)

\(d\) :

Jet diameter (\(d=0.003\) m)

\(T_0\) :

Total temperature of the jet air (K)

\(T_{\infty }\) :

Freestream temperature (K)

\(v_{\rm j}, v_{\infty }\) :

Velocities: jet, freestream (m/s)

\(x, y, z\) :

Coordinates: chord, breadth, upward (m)

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Acknowledgments

This work was financed by the DLR projects “STELAR” and “iPSP2”. The assistance of the technical and scientific staff at the German-Dutch wind-tunnel association, the DLR institute of aeroelasticity, the DLR institute of aerodynamics and flow technology and the DLR workshops is gratefully acknowledged.

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Authors and Affiliations

  1. German Aerospace Center (DLR), Bunsenstrasse 10, 37073 , Göttingen, Germany

    A. D. Gardner, C. Klein, W. E. Sachs, U. Henne, H. Mai & K. Richter

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  1. A. D. Gardner
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  2. C. Klein
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  3. W. E. Sachs
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  4. U. Henne
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  5. H. Mai
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  6. K. Richter
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Correspondence to A. D. Gardner.

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Gardner, A.D., Klein, C., Sachs, W.E. et al. Investigation of three-dimensional dynamic stall on an airfoil using fast-response pressure-sensitive paint. Exp Fluids 55, 1807 (2014). https://doi.org/10.1007/s00348-014-1807-4

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  • DOI: https://doi.org/10.1007/s00348-014-1807-4

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