Boundary Layer Control Using Micro-Electromechanical systems (MEMS)

Abstract

This study investigated the use of MEMS based devices to control the boundary layer separation from a circular cylinder in cross flow. Velocity profiles were measured experimentally in a low speed wind tunnel. Momentum thickness was measured as the primary way to determine a change in the flow field. The goal was to determine the angular location and frequency of operation that would provide an effect on the boundary layer of the cylinder. A 25% reduction of momentum loss in the cylinder wake was detected with an optimal angle of 69 degrees and an optimal frequency of operation equal to that of the shedding frequency of the cylinder.

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 2002
Accession Number
ADA401590

Entities

People

  • David M. Borgeson

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Advanced Electronics
  • Energy and Power Technologies
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Air Force Research Laboratories
  • Boundary Layer
  • Boundary Layer Control
  • Cross Flow
  • Flow
  • Flow Fields
  • Fluid Flow
  • Frequency
  • Layers
  • Measurement
  • Microelectromechanical Systems
  • Pressure Gradients
  • Pressure Transducers
  • Static Pressure
  • Two Dimensional
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Control Systems Engineering.
  • Fluid Mechanics and Fluid Dynamics.
  • Integrated Circuit Design and Technology.

Technology Areas

  • Microelectronics
  • Microelectronics - Microelectromechanical Systems