Reduced order modeling of flow over a NACA 0015 airfoil for control application

E. Caraballo, T. Sullivan, Jesse C Little

Research output: Chapter in Book/Report/Conference proceedingConference contribution

1 Citation (Scopus)

Abstract

Reduced order models that can capture and predict general flow characteristics are essential for closed-loop flow control around aerodynamic bodies. This research tests Galerkin based reduced order models using a proper orthogonal decomposition method to obtain a set of modes derived from experimental data to predict the flow over a NACA-0015 airfoil. Three methodologies are used to derive the models: the original POD Galerkin projection method, a modified version that includes a viscous dissipation term, and a new approach that uses a transfer parameter term to adjust the POD modes. Each of the models is tested on the airfoil at incident angles ranging from α=20 degree; to α=10 degree for the baseline flow and a flow forced at 1250 Hz by nanosecond dielectric barrier discharge plasma actuators. The results showed that the two modified reduced order models were most successful in predicting the time evolution coefficient using between 8 and 12 POD modes for their calculations. At this point, there was no clear indication that one method worked better than the other for the baseline or forced flow, or for a particular angle of attack of the airfoil. The behavior of the transfer parameter versus the angle of attack was investigated in order to find a predictable trend that would reduce the overall computational time, but no clear trend has been observed at this point.

Original languageEnglish (US)
Title of host publicationAIAA AVIATION 2014 -7th AIAA Flow Control Conference
PublisherAmerican Institute of Aeronautics and Astronautics Inc.
ISBN (Print)9781624102929
StatePublished - 2014
EventAIAA AVIATION 2014 -7th AIAA Flow Control Conference 2014 - Atlanta, GA, United States
Duration: Jun 16 2014Jun 20 2014

Other

OtherAIAA AVIATION 2014 -7th AIAA Flow Control Conference 2014
CountryUnited States
CityAtlanta, GA
Period6/16/146/20/14

Fingerprint

Airfoils
Angle of attack
Flow control
Aerodynamics
Actuators
Decomposition
Plasmas

ASJC Scopus subject areas

  • Aerospace Engineering
  • Mechanical Engineering

Cite this

Caraballo, E., Sullivan, T., & Little, J. C. (2014). Reduced order modeling of flow over a NACA 0015 airfoil for control application. In AIAA AVIATION 2014 -7th AIAA Flow Control Conference American Institute of Aeronautics and Astronautics Inc..

Reduced order modeling of flow over a NACA 0015 airfoil for control application. / Caraballo, E.; Sullivan, T.; Little, Jesse C.

AIAA AVIATION 2014 -7th AIAA Flow Control Conference. American Institute of Aeronautics and Astronautics Inc., 2014.

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Caraballo, E, Sullivan, T & Little, JC 2014, Reduced order modeling of flow over a NACA 0015 airfoil for control application. in AIAA AVIATION 2014 -7th AIAA Flow Control Conference. American Institute of Aeronautics and Astronautics Inc., AIAA AVIATION 2014 -7th AIAA Flow Control Conference 2014, Atlanta, GA, United States, 6/16/14.
Caraballo E, Sullivan T, Little JC. Reduced order modeling of flow over a NACA 0015 airfoil for control application. In AIAA AVIATION 2014 -7th AIAA Flow Control Conference. American Institute of Aeronautics and Astronautics Inc. 2014
Caraballo, E. ; Sullivan, T. ; Little, Jesse C. / Reduced order modeling of flow over a NACA 0015 airfoil for control application. AIAA AVIATION 2014 -7th AIAA Flow Control Conference. American Institute of Aeronautics and Astronautics Inc., 2014.
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