The Effects of Roughness at High Reynolds Numbers on the Lift and Drag Characteristics of Three Thick Airfoils

Abstract

Three 22% thick airfoils were tested at Reynolds Numbers 6 to 26 X 10 6th power with roughness strips on the surfaces. Roughened airfoils showed favorable scale effects over entire range tested. Drag coefficients. Maximum lift coefficients of NACA airfoils tested were not affected by roughness strip at 20 to 30% of chord behind leading edge. Lift/draft ratio indicates superiority of NACA 63 (420)-422 airfoil and inferiority of Davis airfoil

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Document Details

Document Type
Technical Report
Publication Date
Aug 01, 1944
Accession Number
ADA800578

Entities

People

  • Frank T. Abbott Jr.
  • Harold R. Turner Jr.

Organizations

  • Langley Research Center

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Aeronautical Laboratories
  • Aeronautics
  • Aircrafts
  • Airfoils
  • Airplanes
  • Boundary Layer
  • Coefficients
  • Drag
  • Fluid Mechanics
  • Leading Edges
  • Low Drag
  • Low Drag Airfoils
  • Pressure Distribution
  • Pressure Measurement
  • Reynolds Number
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.