EXPERIMENTAL PERFORMANCE OF NOZZLES HAVING AREA RATIOS UP TO 300 ON JP-4 FUEL - LIQUID-OXYGEN ROCKET ENGINE

Abstract

4000-POUND-THRUST ROCKET ENGINE AT A CHAMBER PRESSURE OF 600 PSIA. Conic nozzles with area ratios of 8 and 25 had vacuum thrust coefficients at peak specific impulse equal to the values for theoretical frozen expansion. For conic nozzles having area ratios of 50, 100, 200 and 300 the thrust coefficients were higher than those for frozen expansion and equal to approximately 95% of the equilibrium expansion values. The arearatio-200 bell-shaped nozzles, which were 58% as long as the area-ratio-200, 15 degree half-angle conic nozzle, had thrust coefficients of 1.96, compared with 2.04 for the conic. (Author)

Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1961
Accession Number
AD0257281

Entities

People

  • J. Calvin Lovell
  • Nick E. Samanich

Organizations

  • National Aeronautics and Space Administration

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Coefficients
  • Engines
  • Liquid Oxygen
  • Rocket Engines
  • Rockets
  • Specific Impulse
  • Thrust

Readers

  • Combustion and Flow Dynamics.
  • Fluid Dynamics.