Wing-Tunnel Investigation at High Subsonic Speeds of the Lateral-Control Characteristics of an Aileron and a Stepped Spoiler on a Wing With Leading Edge Swept Back 51.3 Degrees

One of 5,165 reports in the series: NACA Research Memorandums available on this site.
Thumbnail image of item number 1 in: 'Wing-Tunnel Investigation at High Subsonic Speeds of the Lateral-Control Characteristics of an Aileron and a Stepped Spoiler on a Wing With Leading Edge Swept Back 51.3 Degrees'.
Thumbnail image of item number 2 in: 'Wing-Tunnel Investigation at High Subsonic Speeds of the Lateral-Control Characteristics of an Aileron and a Stepped Spoiler on a Wing With Leading Edge Swept Back 51.3 Degrees'.
Thumbnail image of item number 3 in: 'Wing-Tunnel Investigation at High Subsonic Speeds of the Lateral-Control Characteristics of an Aileron and a Stepped Spoiler on a Wing With Leading Edge Swept Back 51.3 Degrees'.
Thumbnail image of item number 4 in: 'Wing-Tunnel Investigation at High Subsonic Speeds of the Lateral-Control Characteristics of an Aileron and a Stepped Spoiler on a Wing With Leading Edge Swept Back 51.3 Degrees'.
Showing 1-4 of 35 pages in this report.

PDF Version Also Available for Download.

Description

Report presenting a wind-tunnel investigation through a speed range from Mach number 0.30 to 0.90 to determine the lateral-control characteristics of a 20-percent-chord by 39-percent-semispan aileron and a 60-percent-semispan stepped spoilers on a semispan-wing model with aspect ratio of 3.06 with 51.3 degrees sweepback of the wing leading edge. The aileron rolling effectiveness decreased as the Mach number increased, while the spoiler rolling-moment effectiveness decreased with Mach number.

Physical Description

34 p. : ill.

Creation Information

Schneiter, Leslie E. & Hagerman, John R. June 7, 1949.

Context

This report is part of the collection entitled: National Advisory Committee for Aeronautics Collection and one other and was provided by UNT Libraries Government Documents Department to Digital Library, a digital repository hosted by the UNT Libraries. It has been viewed 190 times . More information about this report can be viewed below.

Who

People and organizations associated with either the creation of this report or its content.

Authors

Originator

Provided By

UNT Libraries Government Documents Department

Serving as both a federal and a state depository library, the UNT Libraries Government Documents Department maintains millions of items in a variety of formats. The department is a member of the FDLP Content Partnerships Program and an Affiliated Archive of the National Archives.

About | Browse this Partner

Contact Us

Corrections Questions

What

Descriptive information to help identify this report. Follow the links below to find similar items on the Digital Library.

Titles

  • Main Title: Wing-Tunnel Investigation at High Subsonic Speeds of the Lateral-Control Characteristics of an Aileron and a Stepped Spoiler on a Wing With Leading Edge Swept Back 51.3 Degrees
  • Series Title: NACA Research Memorandums

Description

Report presenting a wind-tunnel investigation through a speed range from Mach number 0.30 to 0.90 to determine the lateral-control characteristics of a 20-percent-chord by 39-percent-semispan aileron and a 60-percent-semispan stepped spoilers on a semispan-wing model with aspect ratio of 3.06 with 51.3 degrees sweepback of the wing leading edge. The aileron rolling effectiveness decreased as the Mach number increased, while the spoiler rolling-moment effectiveness decreased with Mach number.

Physical Description

34 p. : ill.

Language

Item Type

Identifier

Unique identifying numbers for this report in the Digital Library or other systems.

  • Accession or Local Control No: 93R15142
  • URL: http://hdl.handle.net/2060/19930085852 External Link
  • Report No.: NACA-RM-L9D06
  • Center for AeroSpace Information Number: 19930085852
  • Archival Resource Key: ark:/67531/metadc58204

Collections

This report is part of the following collections of related materials.

National Advisory Committee for Aeronautics Collection

The National Advisory Committee for Aeronautics (NACA) was a U.S. federal agency founded on March 3, 1915 to undertake, promote, and institutionalize aeronautical research. On October 1, 1958 the agency was dissolved, and its assets and personnel transferred to the newly created National Aeronautics and Space Administration (NASA).

About | Browse this Collection

Technical Report Archive and Image Library

This selection of materials from the Technical Report Archive and Image Library (TRAIL) includes hard-to-find reports published by various government agencies. The technical publications contain reports, images, and technical descriptions of research performed for U.S. government agencies. Topics range from mining, desalination, and radiation to broader physics, biology, and chemistry studies. Some reports include maps, foldouts, blueprints, and other oversize materials.

About | Browse this Collection

What responsibilities do I have when using this report?

Digital Files

When

Dates and time periods associated with this report.

Creation Date

  • June 7, 1949

Added to The UNT Digital Library

  • Nov. 16, 2011, 7:33 a.m.

Description Last Updated

  • July 23, 2018, 3:24 p.m.

Usage Statistics

When was this report last used?

Yesterday: 0
Past 30 days: 0
Total Uses: 190
More Statistics

Interact With This Report

Here are some suggestions for what to do next.

Start Reading

Thumbnail image of item number 1 in: 'Wing-Tunnel Investigation at High Subsonic Speeds of the Lateral-Control Characteristics of an Aileron and a Stepped Spoiler on a Wing With Leading Edge Swept Back 51.3 Degrees'.
Thumbnail image of item number 2 in: 'Wing-Tunnel Investigation at High Subsonic Speeds of the Lateral-Control Characteristics of an Aileron and a Stepped Spoiler on a Wing With Leading Edge Swept Back 51.3 Degrees'.
Thumbnail image of item number 3 in: 'Wing-Tunnel Investigation at High Subsonic Speeds of the Lateral-Control Characteristics of an Aileron and a Stepped Spoiler on a Wing With Leading Edge Swept Back 51.3 Degrees'.
Thumbnail image of item number 4 in: 'Wing-Tunnel Investigation at High Subsonic Speeds of the Lateral-Control Characteristics of an Aileron and a Stepped Spoiler on a Wing With Leading Edge Swept Back 51.3 Degrees'.

PDF Version Also Available for Download.

Citations, Rights, Re-Use

International Image Interoperability Framework

IIF Logo

We support the IIIF Presentation API

Links for Robots

Helpful links in machine-readable formats.

Archival Resource Key (ARK)

International Image Interoperability Framework (IIIF)

Metadata Formats

Images

URLs

Stats

Schneiter, Leslie E. & Hagerman, John R. Wing-Tunnel Investigation at High Subsonic Speeds of the Lateral-Control Characteristics of an Aileron and a Stepped Spoiler on a Wing With Leading Edge Swept Back 51.3 Degrees, report, June 7, 1949; (digital.library.unt.edu/ark:/67531/metadc58204/: accessed February 18, 2019), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.