Effects of a Fuselage and Various High-Lift and Stall-Control Flaps on Aerodynamic Characteristics in Ptich of an NACA 64 Series 40 Degree Swept-Back Wing

Abstract

Wind-tunnel tests were carried out to determine low-speed lift, drag, and pitching moment of the wing tested alone, with various flaps, and in various combinations with the fuselage having 10.2:1 fineness ratio. The results are given in graphs. Rolling-moment characteristics are included in some instances. The locations of aerodynamic centers are given for some configurations and for various wing-fuselage combinations. The table gives characteristics for Reynolds No. 6,840,000 for comparing effects of various flaps. NOTE: Requests for copies of this report must be addressed to: N.A.C.A., Washington, DC

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Document Details

Document Type
Technical Report
Publication Date
May 01, 1947
Accession Number
ADA800540

Entities

People

  • D. W. Connor
  • Robert H. Neely

Organizations

  • Langley Research Center

Tags

Communities of Interest

  • Cyber

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Aerodynamic Configurations
  • Aspect Ratio
  • Control Surfaces
  • Fineness Ratio
  • Flaps (Control Surfaces)
  • High Lift
  • Leading Edge Flaps
  • Leading Edges
  • Reynolds Number
  • Spars
  • Split Flaps
  • Surfaces
  • Sweptback Wings
  • Trailing Edges
  • Wing Flaps
  • Wing Tips

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Technical Research and Report Writing.