Effects of internal-area distribution, spike translation, and throat boundary-layer control on performance of a double-cone axisymmetric inlet at Mach numbers from 3.0 to 2.0

One of 5,163 reports in the series: NACA Research Memorandums available on this site.
Thumbnail image of item number 1 in: 'Effects of internal-area distribution, spike translation, and throat boundary-layer control on performance of a double-cone axisymmetric inlet at Mach numbers from 3.0 to 2.0'.
Thumbnail image of item number 2 in: 'Effects of internal-area distribution, spike translation, and throat boundary-layer control on performance of a double-cone axisymmetric inlet at Mach numbers from 3.0 to 2.0'.
Thumbnail image of item number 3 in: 'Effects of internal-area distribution, spike translation, and throat boundary-layer control on performance of a double-cone axisymmetric inlet at Mach numbers from 3.0 to 2.0'.
Thumbnail image of item number 4 in: 'Effects of internal-area distribution, spike translation, and throat boundary-layer control on performance of a double-cone axisymmetric inlet at Mach numbers from 3.0 to 2.0'.
Showing 1-4 of 30 pages in this report.

PDF Version Also Available for Download.

Description

Report presenting an investigation to determine the effects of initial subsonic diffusion rate, variable geometry, and throat boundary-layer control on the performance of an axisymmetric double-cone inlet. Major gains in performance at higher Mach numbers were obtained with boundary-layer control in the form of a ram scoop at the throat. Results regarding the effect of internal-area distribution, effect of spike translation, and effect of throat boundary-layer control are provided.

Physical Description

27 p. : ill.

Creation Information

Conners, James F.; Lovell, J. Calvin & Wise, George A. August 30, 1957.

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 65 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: Effects of internal-area distribution, spike translation, and throat boundary-layer control on performance of a double-cone axisymmetric inlet at Mach numbers from 3.0 to 2.0
  • Series Title: NACA Research Memorandums

Description

Report presenting an investigation to determine the effects of initial subsonic diffusion rate, variable geometry, and throat boundary-layer control on the performance of an axisymmetric double-cone inlet. Major gains in performance at higher Mach numbers were obtained with boundary-layer control in the form of a ram scoop at the throat. Results regarding the effect of internal-area distribution, effect of spike translation, and effect of throat boundary-layer control are provided.

Physical Description

27 p. : ill.

Language

Item Type

Identifier

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

  • Accession or Local Control No: 93R19074
  • URL: http://hdl.handle.net/2060/19930089784 External Link
  • Report No.: NACA-RM-E57F03
  • Center for AeroSpace Information Number: 19930089784
  • Archival Resource Key: ark:/67531/metadc63620

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

  • August 30, 1957

Added to The UNT Digital Library

  • Nov. 17, 2011, 10:13 p.m.

Description Last Updated

  • April 17, 2018, 9:09 a.m.

Usage Statistics

When was this report last used?

Yesterday: 0
Past 30 days: 1
Total Uses: 65
More Statistics

Interact With This Report

Here are some suggestions for what to do next.

Start Reading

Thumbnail image of item number 1 in: 'Effects of internal-area distribution, spike translation, and throat boundary-layer control on performance of a double-cone axisymmetric inlet at Mach numbers from 3.0 to 2.0'.
Thumbnail image of item number 2 in: 'Effects of internal-area distribution, spike translation, and throat boundary-layer control on performance of a double-cone axisymmetric inlet at Mach numbers from 3.0 to 2.0'.
Thumbnail image of item number 3 in: 'Effects of internal-area distribution, spike translation, and throat boundary-layer control on performance of a double-cone axisymmetric inlet at Mach numbers from 3.0 to 2.0'.
Thumbnail image of item number 4 in: 'Effects of internal-area distribution, spike translation, and throat boundary-layer control on performance of a double-cone axisymmetric inlet at Mach numbers from 3.0 to 2.0'.

PDF Version Also Available for Download.

Citations, Rights, Re-Use

Conners, James F.; Lovell, J. Calvin & Wise, George A. Effects of internal-area distribution, spike translation, and throat boundary-layer control on performance of a double-cone axisymmetric inlet at Mach numbers from 3.0 to 2.0, report, August 30, 1957; (digital.library.unt.edu/ark:/67531/metadc63620/: accessed April 27, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.