Wind-tunnel investigation of the effect of aspect ratio and chordwise location on effectiveness of plain spoilers on thin untapered wings at transonic speeds Metadata

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Title

  • Main Title Wind-tunnel investigation of the effect of aspect ratio and chordwise location on effectiveness of plain spoilers on thin untapered wings at transonic speeds
  • Series Title NACA Research Memorandums

Creator

  • Author: Hammond, Alexander D.
    Creator Type: Personal

Contributor

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

Date

  • Creation: 1956-09-26

Language

  • English

Description

  • Content Description: From Summary: "A wind-tunnel investigation has been made in the Langley high-speed 7- by 10-foot wind tunnel by use of the transonic-bump technique to study the effectiveness of spoiler-type controls on 9 unswept untapered wings. Full-span spoilers, projected to 7.5 percent wing chord along the 40-, 60-, 80-, and 100-percent wing chord lines, were tested on wings of aspect ratio 1 to 6 at Mach numbers from 0.6 to 1.10. Most of the data are presented without analysis."
  • Physical Description: 61 p. : ill.

Subject

  • Keyword: aircraft spoilers
  • 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: 93R18636
  • URL: http://hdl.handle.net/2060/19930089346
  • Report No.: NACA-RM-L56F20
  • Center for AeroSpace Information Number: 19930089346
  • Archival Resource Key: ark:/67531/metadc62671
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