Investigation with an Interferometer of the Flow Around a Circular-Arc Airfoil at Mach Numbers Between 0.6 and 0.9

Abstract

The flow around a 12-percent-thick circular-arc airfoil at zero incidence was observed with an interferometer for small increments of free-stream Mach number from 0.609 to 0.896 with laminar and turbulent boundary layers. Mach number contours in the flow field and Mach number and pressure distributions on the airfoil were obtained. Conditions were determined along and at the bases of the shock waves that interacted with the turbulent boundary layer on the airfoil.

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Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1952
Accession Number
ADA377087

Entities

People

  • George P. Wood
  • Paul B. Gooderum

Organizations

  • National Aeronautics and Space Administration

Tags

DTIC Thesaurus Topics

  • Aeronautical Laboratories
  • Barometric Pressure
  • Boundary Layer
  • Dynamic Pressure
  • Experimental Data
  • Flow Fields
  • Free Stream
  • Laminar Boundary Layer
  • Layers
  • Leading Edges
  • Mach Number
  • Pressure Distribution
  • Pressure Measurement
  • Shock Waves
  • Static Pressure
  • Turbulent Boundary Layer
  • Waves

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Fluid Mechanics and Fluid Dynamics.