Wind-Tunnel Investigation of a Low-Drag Airfoil Section with a Double Slotted Flap

Abstract

Tests were made of an 0.309-chord double-slotted flap on an NACA 65, 3-118, a equals 1.0 airfoil section to determine drag, lift, and pitching-moment characteristics for a range of flap deflections. Results indicate that combination of a low-drag airfoil and a double-slotted flap, of which the two parts moved as a single unit, gave higher maximum lift coefficients than have been obtained with plain, split, or slotted flaps on low-drag airfoils. Pitching moments were comparable to those obtained with other high-lift devices on conventional airfoils for similar lift coefficients.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Sep 01, 1943
Accession Number
ADA800659

Entities

People

  • Seymour M. Bogdonoff

Organizations

  • Langley Research Center

Tags

DTIC Thesaurus Topics

  • Aeronautical Laboratories
  • Aeronautics
  • Airfoils
  • Coefficients
  • Deflection
  • Drag
  • High Lift
  • High Lift Devices
  • Low Drag
  • Low Drag Airfoils
  • Slotted Flaps
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.