Investigation of NACA 65(112)A111 (Approx.) Airfoil with 0.35-Chord Slotted Flap at Reynolds Numbers up to 25 Million

Abstract

Wind-tunnel investigation of the NACA 65 (112) A111 airfoil with 0.35-chord slotted flap was made at Reynolds Numbers ranging from 2.4 x 10 6, Results indicated that for this airfoil and flap, the flap deflection for highest maximum section lift coefficient decreased, and the flap position for highest c max moved rearward and upward as Reynolds number increased from 2.4 x 10 6 to 9.0 x 10 6. Maximum life coefficient for this airfoil with flap retracted and with flap deflected generally increased with Reynolds number up to about 15.0 x 10 6 and then decreased slightly.

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Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1947
Accession Number
ADA801524

Entities

People

  • Stanley F. Racisz

Organizations

  • National Aeronautics and Space Administration

Tags

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Aeronautical Laboratories
  • Aeronautics
  • Airfoils
  • Aluminum Alloys
  • Boundary Layer
  • Coefficients
  • Deflection
  • Drag
  • Flow
  • Leading Edges
  • Low Angles
  • Mach Number
  • Reynolds Number
  • Slotted Flaps
  • Test Methods
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Mathematics or Statistics