An Experimental Investigation of Lift and Roll Control Using Plasma Actuators

Doctoral Dissertation
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Abstract

This work describes an experimental investigation into the use of plasma actuators for lift and roll control. The use of plasma actuators for flow-control applications has been demonstrated extensively in recent years, for example, to postpone flow separation or eliminate Karman shedding behind bluff bodies. The current research describes a unique application of plasma actuators in which the actuators were placed near the trailing edge of a wing or airfoil in an effort to directly control circulation. Experimental data are presented showing the effect that the actuators have on lift, pitch, roll-moment and pressure distribution as a function of angle of attack and wind speed. The experiments are performed in the range of Reynolds numbers Re = 30,000- 370,000 and the angle-of-attack range: -3Ìâå¡ to +10Ìâå¡. The results indicate that the performance of the actuators is strongly influenced by Reynolds number effects. The implications of the results on the application of plasma actuators as lift and roll-control devices are discussed.

Attributes

Attribute NameValues
URN
  • etd-07232010-155520

Author Alexander Vorobiev
Advisor Robert Nelson
Contributor Stanislav Gordeyev, Committee Member
Contributor Flint O. Thomas, Committee Member
Contributor Robert Nelson, Committee Chair
Degree Level Doctoral Dissertation
Degree Discipline Aerospace and Mechanical Engineering
Degree Name PhD
Defense Date
  • 2010-07-16

Submission Date 2010-07-23
Country
  • United States of America

Subject
  • Low-Reynolds Number Flow

  • Lift Control

  • Plasma Actuator

Publisher
  • University of Notre Dame

Language
  • English

Record Visibility and Access Public
Content License
  • All rights reserved

Departments and Units

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