Closed loop control of a flap exposed to harmonic aerodynamic actuation

Clara Marika Velte; Robert Flemming Mikkelsen; Jens Nørkær Sørensen; Teodor  Kaloyanov; Mac Gaunaa

Closed loop control of a flap exposed to harmonic aerodynamic actuation

Clara Marika Velte, Robert Flemming Mikkelsen, Jens Nørkær Sørensen, Teodor Kaloyanov, Mac Gaunaa

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Abstract

Wind tunnel testing of a two-dimensional aerofoil with a load reducing flap has been conducted under the influence of a closed-loop controller (PID). Upstream synthetic perturbations for well-defined testing of the controller were generated by instrumenting the wind tunnel with two fast turning vanes placed in front of the main test wing. These were situated symmetrically above and below the airfoil in a way that created a fast turning of the air flow without directly affecting the boundary layer on the test airfoil. The Reynolds number was Re=500.000. The PID-controlled flap was able to alleviate the load variations with reductions above 80% for reduced frequencies up to k = 0.028 and nearly 70% at k=0.054. At about 0.108 and higher a different strategy is needed for the present setup as the reduction is low or even negative.

Original language	English
Title of host publication	Proceedings of Torque 2012, The science of making torque from wind
Number of pages	7
Publication date	2012
Publication status	Published - 2012
Event	The science of Making Torque from Wind 2012: 4th scientific conference - Universität Oldenburg, Oldenburg, Germany Duration: 9 Oct 2012 → 11 Oct 2012 http://www.forwind.de/makingtorque/Home.html

Conference

Conference	The science of Making Torque from Wind 2012
Location	Universität Oldenburg
Country/Territory	Germany
City	Oldenburg
Period	09/10/2012 → 11/10/2012
Internet address	http://www.forwind.de/makingtorque/Home.html

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@inproceedings{7a69337620c241fd9aa2f0f194d66529,

title = "Closed loop control of a flap exposed to harmonic aerodynamic actuation",

abstract = "Wind tunnel testing of a two-dimensional aerofoil with a load reducing flap has been conducted under the influence of a closed-loop controller (PID). Upstream synthetic perturbations for well-defined testing of the controller were generated by instrumenting the wind tunnel with two fast turning vanes placed in front of the main test wing. These were situated symmetrically above and below the airfoil in a way that created a fast turning of the air flow without directly affecting the boundary layer on the test airfoil. The Reynolds number was Re=500.000. The PID-controlled flap was able to alleviate the load variations with reductions above 80% for reduced frequencies up to k = 0.028 and nearly 70% at k=0.054. At about 0.108 and higher a different strategy is needed for the present setup as the reduction is low or even negative.",

author = "Velte, {Clara Marika} and Mikkelsen, {Robert Flemming} and S{\o}rensen, {Jens N{\o}rk{\ae}r} and Teodor Kaloyanov and Mac Gaunaa",

year = "2012",

language = "English",

booktitle = "Proceedings of Torque 2012, The science of making torque from wind",

note = "The science of Making Torque from Wind 2012 : 4th scientific conference ; Conference date: 09-10-2012 Through 11-10-2012",

url = "http://www.forwind.de/makingtorque/Home.html",

}

TY - GEN

T1 - Closed loop control of a flap exposed to harmonic aerodynamic actuation

AU - Velte, Clara Marika

AU - Mikkelsen, Robert Flemming

AU - Sørensen, Jens Nørkær

AU - Kaloyanov, Teodor

AU - Gaunaa, Mac

PY - 2012

Y1 - 2012

N2 - Wind tunnel testing of a two-dimensional aerofoil with a load reducing flap has been conducted under the influence of a closed-loop controller (PID). Upstream synthetic perturbations for well-defined testing of the controller were generated by instrumenting the wind tunnel with two fast turning vanes placed in front of the main test wing. These were situated symmetrically above and below the airfoil in a way that created a fast turning of the air flow without directly affecting the boundary layer on the test airfoil. The Reynolds number was Re=500.000. The PID-controlled flap was able to alleviate the load variations with reductions above 80% for reduced frequencies up to k = 0.028 and nearly 70% at k=0.054. At about 0.108 and higher a different strategy is needed for the present setup as the reduction is low or even negative.

AB - Wind tunnel testing of a two-dimensional aerofoil with a load reducing flap has been conducted under the influence of a closed-loop controller (PID). Upstream synthetic perturbations for well-defined testing of the controller were generated by instrumenting the wind tunnel with two fast turning vanes placed in front of the main test wing. These were situated symmetrically above and below the airfoil in a way that created a fast turning of the air flow without directly affecting the boundary layer on the test airfoil. The Reynolds number was Re=500.000. The PID-controlled flap was able to alleviate the load variations with reductions above 80% for reduced frequencies up to k = 0.028 and nearly 70% at k=0.054. At about 0.108 and higher a different strategy is needed for the present setup as the reduction is low or even negative.

M3 - Article in proceedings

BT - Proceedings of Torque 2012, The science of making torque from wind

T2 - The science of Making Torque from Wind 2012

Y2 - 9 October 2012 through 11 October 2012

ER -

Closed loop control of a flap exposed to harmonic aerodynamic actuation

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