Linear unsteady aerodynamic models from wind tunnel measurements

Steven L. Brunton; Clarence W. Rowley; David R. Williams

doi:10.2514/6.2011-3581

Linear unsteady aerodynamic models from wind tunnel measurements

Steven L. Brunton, Clarence W. Rowley, David R. Williams

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution

1 Scopus citations

Abstract

Linear unsteady aerodynamic models are obtained for a NACA 0006 airfoil in a wind tunnel experiment at Reynolds number 65,000. A family of system identification maneuvers, based on a canonical step-up, hold maneuver, are specifically designed to extract relevant unsteady information from phase averaged wind tunnel measurements. Linear models based on these maneuvers are constructed using OKID/ERA for the case of pitching about α0 = 0° and α0 = 10°, as well as the case of pure plunge. It is shown that the identified models are more accurate than Theodorsen's model for all maneuvers, especially those at larger base angle of attack.

Original language	English (US)
Title of host publication	41st AIAA Fluid Dynamics Conference and Exhibit
Publisher	American Institute of Aeronautics and Astronautics Inc.
ISBN (Print)	9781600869471
DOIs	https://doi.org/10.2514/6.2011-3581
State	Published - 2011
Event	41st AIAA Fluid Dynamics Conference and Exhibit 2011 - Honolulu, HI, United States Duration: Jun 27 2011 → Jun 30 2011

Publication series

Name	41st AIAA Fluid Dynamics Conference and Exhibit

Other

Other	41st AIAA Fluid Dynamics Conference and Exhibit 2011
Country/Territory	United States
City	Honolulu, HI
Period	6/27/11 → 6/30/11

All Science Journal Classification (ASJC) codes

Fluid Flow and Transfer Processes
Energy Engineering and Power Technology
Aerospace Engineering
Mechanical Engineering

Access to Document

10.2514/6.2011-3581

Cite this

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title = "Linear unsteady aerodynamic models from wind tunnel measurements",

abstract = "Linear unsteady aerodynamic models are obtained for a NACA 0006 airfoil in a wind tunnel experiment at Reynolds number 65,000. A family of system identification maneuvers, based on a canonical step-up, hold maneuver, are specifically designed to extract relevant unsteady information from phase averaged wind tunnel measurements. Linear models based on these maneuvers are constructed using OKID/ERA for the case of pitching about α0 = 0° and α0 = 10°, as well as the case of pure plunge. It is shown that the identified models are more accurate than Theodorsen's model for all maneuvers, especially those at larger base angle of attack.",

author = "Brunton, {Steven L.} and Rowley, {Clarence W.} and Williams, {David R.}",

year = "2011",

doi = "10.2514/6.2011-3581",

language = "English (US)",

isbn = "9781600869471",

series = "41st AIAA Fluid Dynamics Conference and Exhibit",

publisher = "American Institute of Aeronautics and Astronautics Inc.",

booktitle = "41st AIAA Fluid Dynamics Conference and Exhibit",

note = "41st AIAA Fluid Dynamics Conference and Exhibit 2011 ; Conference date: 27-06-2011 Through 30-06-2011",

}

Brunton, SL, Rowley, CW & Williams, DR 2011, Linear unsteady aerodynamic models from wind tunnel measurements. in 41st AIAA Fluid Dynamics Conference and Exhibit. 41st AIAA Fluid Dynamics Conference and Exhibit, American Institute of Aeronautics and Astronautics Inc., 41st AIAA Fluid Dynamics Conference and Exhibit 2011, Honolulu, HI, United States, 6/27/11. https://doi.org/10.2514/6.2011-3581

Linear unsteady aerodynamic models from wind tunnel measurements. / Brunton, Steven L.; Rowley, Clarence W.; Williams, David R.
41st AIAA Fluid Dynamics Conference and Exhibit. American Institute of Aeronautics and Astronautics Inc., 2011. (41st AIAA Fluid Dynamics Conference and Exhibit).

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution

TY - GEN

T1 - Linear unsteady aerodynamic models from wind tunnel measurements

AU - Brunton, Steven L.

AU - Rowley, Clarence W.

AU - Williams, David R.

PY - 2011

Y1 - 2011

N2 - Linear unsteady aerodynamic models are obtained for a NACA 0006 airfoil in a wind tunnel experiment at Reynolds number 65,000. A family of system identification maneuvers, based on a canonical step-up, hold maneuver, are specifically designed to extract relevant unsteady information from phase averaged wind tunnel measurements. Linear models based on these maneuvers are constructed using OKID/ERA for the case of pitching about α0 = 0° and α0 = 10°, as well as the case of pure plunge. It is shown that the identified models are more accurate than Theodorsen's model for all maneuvers, especially those at larger base angle of attack.

AB - Linear unsteady aerodynamic models are obtained for a NACA 0006 airfoil in a wind tunnel experiment at Reynolds number 65,000. A family of system identification maneuvers, based on a canonical step-up, hold maneuver, are specifically designed to extract relevant unsteady information from phase averaged wind tunnel measurements. Linear models based on these maneuvers are constructed using OKID/ERA for the case of pitching about α0 = 0° and α0 = 10°, as well as the case of pure plunge. It is shown that the identified models are more accurate than Theodorsen's model for all maneuvers, especially those at larger base angle of attack.

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T3 - 41st AIAA Fluid Dynamics Conference and Exhibit

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PB - American Institute of Aeronautics and Astronautics Inc.

T2 - 41st AIAA Fluid Dynamics Conference and Exhibit 2011

Y2 - 27 June 2011 through 30 June 2011

ER -

Linear unsteady aerodynamic models from wind tunnel measurements

Abstract

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Other

All Science Journal Classification (ASJC) codes

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