Notes on the theoretical characteristics of two-dimensional supersonic airfoils

One of 4,107 reports in the series: NACA Technical Notes available on this site.

PDF Version Also Available for Download.

Description

The shock expansion method of the NACA TN No. 1143 was used to determine the principal aerodynamic characteristics of two-dimensional supersonic airfoils. A discussion is given of the effect of thickness ratio, free-stream Mach number, angle of attack, camber, thickness distribution, and aileron deflection. The calculations indicated that the minimum drag of supersonic airfoils is obtained when the maximum thickness is behind the 0.50 chord. The center of pressure obtained for a symmetrical supersonic airfoil was found to be ahead of the 0.50 chord.

Physical Description

[23] p. : ill.

Creation Information

Ivey, H. Reese January 1947.

Context

This report is part of the collection entitled: National Advisory Committee for Aeronautics Collection and was provided by the UNT Libraries Government Documents Department to the UNT Digital Library, a digital repository hosted by the UNT Libraries. It has been viewed 125 times, with 5 in the last month. More information about this report can be viewed below.

Who

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

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.

Contact Us

What

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

Titles

  • Main Title: Notes on the theoretical characteristics of two-dimensional supersonic airfoils
  • Series Title: NACA Technical Notes

Description

The shock expansion method of the NACA TN No. 1143 was used to determine the principal aerodynamic characteristics of two-dimensional supersonic airfoils. A discussion is given of the effect of thickness ratio, free-stream Mach number, angle of attack, camber, thickness distribution, and aileron deflection. The calculations indicated that the minimum drag of supersonic airfoils is obtained when the maximum thickness is behind the 0.50 chord. The center of pressure obtained for a symmetrical supersonic airfoil was found to be ahead of the 0.50 chord.

Physical Description

[23] p. : ill.

Language

Item Type

Identifier

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

  • Accession or Local Control No: 93R11240
  • URL: http://hdl.handle.net/2060/19930081950 External Link
  • Report No.: NACA-TN-1179
  • Center for AeroSpace Information Number: 19930081950
  • Archival Resource Key: ark:/67531/metadc55309

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).

Technical Report Archive and Image Library

The Technical Report Archive & Image Library (TRAIL) identifies, acquires, catalogs, digitizes and provides unrestricted access to U.S. government agency technical reports. The mission of TRAIL is to ensure preservation, discoverability, and persistent open access to government technical publications regardless of form or format.

What responsibilities do I have when using this report?

When

Dates and time periods associated with this report.

Creation Date

  • January 1947

Added to The UNT Digital Library

  • Nov. 14, 2011, 10:28 p.m.

Description Last Updated

  • March 13, 2019, 4:45 p.m.

Usage Statistics

When was this report last used?

Yesterday: 0
Past 30 days: 5
Total Uses: 125

Interact With This Report

Here are some suggestions for what to do next.

Start Reading

PDF Version Also Available for Download.

International Image Interoperability Framework

IIF Logo

We support the IIIF Presentation API

Ivey, H. Reese. Notes on the theoretical characteristics of two-dimensional supersonic airfoils, report, January 1947; (https://digital.library.unt.edu/ark:/67531/metadc55309/: accessed March 28, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.

Back to Top of Screen