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

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Title

  • Main Title Effects of a Fuselage on the Aerodynamic Characteristics of a 42 Degree Sweptback Wing at Reynolds Numbers to 8,000,000
  • Series Title NACA Research Memorandums

Creator

  • Author: Salmi, Reino J.
    Creator Type: Personal
  • Author: Conner, D. William
    Creator Type: Personal
  • Author: Graham, Robert R.
    Creator Type: Personal

Contributor

  • Originator: Langley Aeronautical Laboratory
    Contributor Type: Organization
    Contributor Info: National Advisory Committee for Aeronautics. Langley Aeronautical Lab

Date

  • Creation: 1947-06-10

Language

  • English

Description

  • Content Description: 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.

Subject

  • Keyword: aerodynamics
  • Keyword: split flaps

Collection

  • Name: National Advisory Committee for Aeronautics Collection
    Code: NACA
  • Name: Technical Report Archive and Image Library
    Code: TRAIL

Institution

  • Name: UNT Libraries Government Documents Department
    Code: UNTGD

Rights

  • Rights Access: public
  • Rights License: pd
  • Rights Statement: No Copyright, Unclassified, Unlimited, Publicly available

Resource Type

  • Report

Format

  • Text

Identifier

  • Accession or Local Control No: 93R19636
  • URL: http://hdl.handle.net/2060/19930090346
  • Report No.: NACA-RM-L7E13
  • Center for AeroSpace Information Number: 19930090346
  • Archival Resource Key: ark:/67531/metadc64565