Study of Transient and Unsteady Effects of Plasma Actuation in Transitional Flow over an SD7003 Airfoil

Abstract

The short term transient and long term periodic unsteady effects of pulsed plasma actuation are studied using an unsteady, compressible Navier-Stokes solver for the case of a partially separated transitional flow over an SD7003 airfoil at 4 deg angle of attack and at Re=40,000. Forcing magnitude and its effect on the flow field is examined. Distinctly different behavior is observed parameters are adjusted. The unsteady simulations show that the actuators have a quick transient response, reattaching the separated flow within 2 non-dimensionalized units of time, but nearly independently of the forcing magnitude. Spikes in C(l), C(d), and C(m) are observed during reattachment, most likely due to vortex pairing at the trailing edge.

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Document Details

Document Type
Technical Report
Publication Date
Jan 01, 2011
Accession Number
ADA541901

Entities

People

  • Don Rizzetta
  • Mark Riherd
  • Miguel Visbal
  • Subrata Roy

Organizations

  • Air Force Research Laboratory

Tags

Communities of Interest

  • Advanced Electronics
  • Energy and Power Technologies
  • Space

DTIC Thesaurus Topics

  • Air Force Research Laboratories
  • Aircrafts
  • Boundary Layer
  • Computational Fluid Dynamics
  • Computational Science
  • Equations
  • Flow Fields
  • Fluid Dynamics
  • Fluid Flow
  • Hypervelocity Flow
  • Kinetic Energy
  • Micro Air Vehicles
  • Physics Laboratories
  • Reynolds Number
  • Simulations
  • Turbulent Mixing
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.