Nuclear-Powered Flight. Chapter 4: Preliminary Report on Nuclear Energy for Rocket Propulsion

Abstract

In the comparison of fuels for use in rocket propulsion, probably the most significant parameter is the so-called effective gas velocity or, equivalently, the specific impulse. This quantity is defined by the ratio of thrust to the mass rate of discharge of propulsive gas and is mainly a function of the thermodynamic properties of the gas.

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Document Details

Document Type
Technical Report
Publication Date
Jan 14, 1947
Accession Number
AD1185491

Entities

People

  • F. T. Mcclure
  • R. B. Kershner

Organizations

  • Johns Hopkins University

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Energy
  • Engineering
  • Equations
  • Escape Velocity
  • Graphite
  • Graphitic Materials
  • Heat Loss
  • Heat Transfer
  • Hydrogen
  • Nuclear Reactors
  • Payload
  • Rocket Propulsion
  • Sea Level
  • Specific Impulse
  • Thermodynamic Properties
  • Water Vapor

Fields of Study

  • Physics

Readers

  • Rocket Propulsion.
  • Strategic Security Studies