Skin Friction Measurements for Two Relatively Thick Airfoil Sections at High Reynolds Number (Mesures du Frottement sur Deux Profils Aerodynamiques Assez Epais a Nombres de Reynolds Eleves)

Abstract

This Canadian report describes an experimental investigation of turbulent skin friction for two airfoil sections under conditions of high Reynolds number. Data are presented for an NACA 0020 section at a Mach number of 0.30 and chord Reynolds numbers between 5 and 20 million, and for a 16% thick supercritical section at a Mach number of 0.74 and chord Reynolds numbers between 15 and 25 million. Together with estimates of boundary layer transition location, these data are integrated to determine the skin friction component of total drag. The results are then discussed in terms of observed variation of total drag with Reynolds number.

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Document Details

Document Type
Technical Report
Publication Date
Nov 01, 1984
Accession Number
ADA150021

Entities

People

  • G. M. Elfstrom

Organizations

  • National Research Council Canada

Tags

Communities of Interest

  • Air Platforms
  • Materials and Manufacturing Processes

DTIC Thesaurus Topics

  • Airfoils
  • Boundary Layer
  • Boundary Layer Transition
  • Flow Fields
  • Fluid Dynamics
  • Layers
  • Mach Number
  • Measurement
  • Pressure Distribution
  • Pressure Gradients
  • Reynolds Number
  • Shock Waves
  • Static Pressure
  • Supercritical Airfoils
  • Test Facilities
  • Turbulent Flow
  • Turbulent Mixing

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.
  • Small Business Innovation Research Program (SBIR) EDI Research and Innovation.