Wind-Tunnel Investigation of NACA 66(215)-216, 66,1-212, and 65 sub 1 -212 Airfoils with 0.20-Airfoil-Chord Split Flaps

Abstract

An investigation was carried out in the NACA two-dimensional low-turbulence pressure tunnel of the NACA 66(215)-216, 66,1-212, and 65 sub 1 -212 airfoil sections equipped with split flaps having chords 20 percent of the airfoil chord. The purpose was to determine the maximum-lift characteristics of these low-drag airfoil sections with split flaps. All the present tests were made at a Reynolds number of approximately 6 x 10 (expn 6) and a Mach number of about 0.15.

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Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1944
Accession Number
ADA801567

Entities

People

  • Felicien F. Fullmer Jr.

Organizations

  • National Advisory Committee for Aeronautics

Tags

DTIC Thesaurus Topics

  • Aeronautical Laboratories
  • Aeronautics
  • Airfoils
  • Coefficients
  • Deflection
  • Drag
  • High Lift
  • High Lift Devices
  • Leading Edges
  • Low Drag
  • Low Drag Airfoils
  • Mach Number
  • Reynolds Number
  • Split Flaps
  • Surfaces
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.