Accession Number:

AD0257281

Title:

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

Descriptive Note:

Corporate Author:

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON D C

Personal Author(s):

Report Date:

1961-06-01

Pagination or Media Count:

1.0

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

Subject Categories:

Distribution Statement:

APPROVED FOR PUBLIC RELEASE