Experimental performance of liquid fluorine-liquid ammonia propellant combination in 1000-pound-thrust rocket engines

One of 5,164 reports in the series: NACA Research Memorandums available on this site.

PDF Version Also Available for Download.

Description

"The performance of liquid fluorine and liquid ammonia as a propellant combination was evaluated in 1000-pound-thrust rocket engines operated at a chamber pressure of 600 pounds per square inch absolute. Values of specific impulse, characteristic velocity, thrust coefficient, and heat rejection were obtained as functions of propellant mixture ratio for each of four injectors: a triplet, a showerhead, and two like-on-like types" (p. 1).

Physical Description

32 p. : ill.

Creation Information

Douglass, Howard W. May 13, 1954.

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 93 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.

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: Experimental performance of liquid fluorine-liquid ammonia propellant combination in 1000-pound-thrust rocket engines
  • Series Title: NACA Research Memorandums

Description

"The performance of liquid fluorine and liquid ammonia as a propellant combination was evaluated in 1000-pound-thrust rocket engines operated at a chamber pressure of 600 pounds per square inch absolute. Values of specific impulse, characteristic velocity, thrust coefficient, and heat rejection were obtained as functions of propellant mixture ratio for each of four injectors: a triplet, a showerhead, and two like-on-like types" (p. 1).

Physical Description

32 p. : ill.

Language

Item Type

Identifier

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

  • Accession or Local Control No: 93R17478
  • URL: http://hdl.handle.net/2060/19930088188 External Link
  • Report No.: NACA-RM-E54C17
  • Center for AeroSpace Information Number: 19930088188
  • Archival Resource Key: ark:/67531/metadc60368

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

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.

What responsibilities do I have when using this report?

When

Dates and time periods associated with this report.

Creation Date

  • May 13, 1954

Added to The UNT Digital Library

  • Nov. 17, 2011, 10:13 p.m.

Description Last Updated

  • June 14, 2018, 3:52 p.m.

Usage Statistics

When was this report last used?

Yesterday: 0
Past 30 days: 0
Total Uses: 93

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

Douglass, Howard W. Experimental performance of liquid fluorine-liquid ammonia propellant combination in 1000-pound-thrust rocket engines, report, May 13, 1954; (digital.library.unt.edu/ark:/67531/metadc60368/: accessed September 19, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.