Aerodynamic Characteristics at a Mach Number of 1.25 of a 6-Percent-Thick Triangular Wing and 6- and 9-Percent-Thick Triangular Wings in Combination With a Fuselage: Wing Aspect Ratio 2.31, Biconvex Airfoil Sections Metadata

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Title

  • Main Title Aerodynamic Characteristics at a Mach Number of 1.25 of a 6-Percent-Thick Triangular Wing and 6- and 9-Percent-Thick Triangular Wings in Combination With a Fuselage: Wing Aspect Ratio 2.31, Biconvex Airfoil Sections
  • Series Title NACA Research Memorandums

Creator

  • Author: Hall, Albert W.
    Creator Type: Personal
  • Author: Morris, Garland J.
    Creator Type: Personal

Contributor

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

Date

  • Creation: 1950-05-05

Language

  • English

Description

  • Content Description: Report discussing testing to determine the aerodynamic characteristics of two semispan delta-wing configurations. Information about the lift characteristics, drag characteristics, pitching-moment characteristics, and comparison with other results is provided.
  • Physical Description: 22 p. : ill.

Subject

  • Keyword: aircraft design
  • Keyword: aircraft stability
  • Keyword: aircraft control

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: 93R15481
  • URL: http://hdl.handle.net/2060/19930086191
  • Report No.: NACA-RM-L50D05
  • Center for AeroSpace Information Number: 19930086191
  • Archival Resource Key: ark:/67531/metadc58471
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