The Transonic Oscillating Flap.

Abstract

Numerical experiments for the unsteady transonic flow past a symmetric airfoil with an oscillating flap in free air are carried out for a range of supercritical Mach numbers and reduced frequencies using two newly devised computational schemes. The inviscid results, unhampered by the complicating effects of wind tunnel wall interference and shockwave and boundary layer interaction, evaluate the extent to which the unsteady loading responds linearly to changes in flap deflection and also the dependence of shock excursion amplitude and net unsteady lift and moment coefficients on oscillation frequency. The main conclusions are discussed in light of recent experimental findings. (Author)

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Document Details

Document Type
Technical Report
Publication Date
May 01, 1979
Accession Number
ADA070022

Entities

People

  • Wilson C. Chin

Organizations

  • Boeing

Tags

Communities of Interest

  • Space

DTIC Thesaurus Topics

  • Amplitude
  • Boundaries
  • Boundary Layer
  • Coefficients
  • Deflection
  • Engineering
  • Equations
  • Flow
  • Frequency
  • Layers
  • Mach Number
  • Military Research
  • Oscillation
  • Pressure Distribution
  • Shock
  • Transonic Flow
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Fluid Dynamics.
  • Theoretical Analysis.