Effects of a Fuselage on the Aerodynamic Characteristics of a 42 Degree Sweptback Wing at Reynolds Numbers to 8,000,000

Abstract

Wind-tunnel investigations were made in pitch and yaw with and without split flaps. Presence of the fuselage had negligible effect on values of maximum lift coefficient and slope of lift curve, but caused a destabilizing shift in the rate of change of pitching moment with lift. Effects of fuselage position on drag characteristics were small for wings without flaps, but were appreciable when split flaps were on.

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Document Details

Document Type
Technical Report
Publication Date
Jun 10, 1947
Accession Number
ADA800634

Entities

People

  • D. W. Conner
  • Reino J. Salmi
  • Robert R. Graham

Organizations

  • Langley Research Center

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Aerodynamics
  • Aeronautical Laboratories
  • Aircrafts
  • Aspect Ratio
  • Coefficients
  • Dynamic Pressure
  • Free Stream
  • Fuselages
  • High Angles
  • High Lift
  • Leading Edges
  • Mach Number
  • Reynolds Number
  • Split Flaps
  • Sweptback Wings
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.