CaltechAUTHORS
  A Caltech Library Service

Modeling Dynamic Lift Response to Actuation

An, Xuanhong and Williams, David R. and Eldredge, Jeff and Colonius, Tim (2016) Modeling Dynamic Lift Response to Actuation. In: 54th AIAA Aerospace Sciences Meeting, 4-8 January 2016, San Diego, CA. https://resolver.caltech.edu/CaltechAUTHORS:20190712-112320249

[img] PDF - Submitted Version
See Usage Policy.

1347Kb

Use this Persistent URL to link to this item: https://resolver.caltech.edu/CaltechAUTHORS:20190712-112320249

Abstract

The dynamic lift response of an airfoil to sinusoidal amplitude variations from a synthetic jet actuator was studied. The wing was at a fixed angle of attack, and the actuator operated in a 'burst-mode' with a fixed duty cycle. The actuator burst mplitude was used as a control signal, which was varied between an ‘off ’ condition and the actuator saturation voltage. Three dimensionless frequencies were examined, corresponding to k = [(πfc)/(U∞)] = 0.064, 0.128, and 0.25. Hysteresis loops in the lift increment were observed, whose shapes were dependent on the control frequency. Three different approaches to modeling the lift increment response were explored: a linear convolution approach, a nonlinear time delay and decay model, and a combination of those two. The linear convolution captures the high frequency content of the lift response, but becomes inaccurate when the actuator burst period is less than 3.5 convective times. The time delay and decay model reproduces the low frequency component of the lift response, but not the high frequency. When the control frequency becomes large, (k = 0.25), then the largest time-varying lift increment is produced near the minimum of the actuator voltage.


Item Type:Conference or Workshop Item (Paper)
Related URLs:
URLURL TypeDescription
https://doi.org/10.2514/6.2016-0058DOIConference Paper
https://arc.aiaa.org/doi/10.2514/6.2016-0058PublisherConference Paper
ORCID:
AuthorORCID
Colonius, Tim0000-0003-0326-3909
Additional Information:© 2016 American Institute of Aeronautics and Astronautics. Published Online: 2 Jan 2016. Support by the U.S. Air Force Office of Scientific Research (FA9550-14-1-0328) with program manager Dr. Douglas Smith is gratefully acknowledged.
Funders:
Funding AgencyGrant Number
Air Force Office of Scientific Research (AFOSR)FA9550-14-1-0328
Subject Keywords:Fluid Dynamics
Other Numbering System:
Other Numbering System NameOther Numbering System ID
AIAA Paper2016-0058
Record Number:CaltechAUTHORS:20190712-112320249
Persistent URL:https://resolver.caltech.edu/CaltechAUTHORS:20190712-112320249
Usage Policy:No commercial reproduction, distribution, display or performance rights in this work are provided.
ID Code:97095
Collection:CaltechAUTHORS
Deposited By: Melissa Ray
Deposited On:12 Jul 2019 22:01
Last Modified:03 Oct 2019 21:28

Repository Staff Only: item control page