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Comparative in-flight and wind tunnel investigation of the development of natural and controlled disturbances in the laminar boundary layer of an airfoil

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Abstract

This paper describes in-flight and wind tunnel research into laminar-turbulent transition. Measurements were carried out with a laminar wing glove for a glider (Twin II Grob G103), which could also be used in the large laminar wind tunnel at the Institute for Aerodynamics and Gasdynamics in Stuttgart. The central aspect of the investigation was the survey of the temporal–spatial development and propagation of natural as well as controlled generated waves. For the experiments performed, varied sensor arrays were used which allowed the two-dimensional acquisition of flow information on the glove (surface hot-wire and piezo foil sensors). Thus the amplification and the spatial distribution of the disturbances could be measured and compared in flight as well as in the wind tunnel, beginning with the very early linear amplification stage to the early non-linear stage of transition. For the investigation of controlled transition, multiple spanwise adjacent harmonic point sources were used which were operated independently.

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Abbreviations

A :

Local amplitude of the fluctuations

A 0 :

Initial amplitude of the fluctuations

d E :

Diameter of one hole of the point soure

E :

Voltage

E RMS :

Root mean square of E

E MAX :

Maximum of E

f :

Frequency

f A :

Frequency of the disturbance signal

N :

Growth rate N = ln(A/A 0)

Re c :

Reynolds-number based on the chord

t :

Time

u :

Streamwise velocity

u e :

Local velocity at the edge of the boundary layer

u ∞ :

Velocity of the oncoming flow

x :

Coordinate in streamwise direction along the chord

x/c :

Normalized distance along the chord

x tr/c :

Distance along the chord at transition position

z :

Coordinate in spanwise direction

α:

Angle of attack

ϕ:

Phase shift

Θ:

Oblique angle

DFG:

Deutsche Forschungsgemeinschaft (German Research Foundation)

CTA:

Contant temperature mode

PVDF:

Polyvinylide fluoride

TS:

Tollmien Schlichting

TU:

Turbulence level

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Acknowledgments

Financial support for the research work by the Deutsche Forschungsgemeinschaft (DFG) is gratefully acknowledged. Furthermore, I would like to thank all colleagues involved in the cooperative project for their support.

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  1. Institute for Aeronautics and Astronautics (ILR), Technical University of Berlin, Marchstr. 12-14, 10587, Berlin, Germany

    Inken Peltzer

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Peltzer, I. Comparative in-flight and wind tunnel investigation of the development of natural and controlled disturbances in the laminar boundary layer of an airfoil. Exp Fluids 44, 961–972 (2008). https://doi.org/10.1007/s00348-007-0455-3

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