Accession Number:

AD0258759

Title:

EXPERIMENTAL STUDY OF EFFECTS OF GEOMETRIC VARIABLES ON PERFORMANCE OF CONICAL ROCKET-ENGINE EXHAUST NOZZLES

Descriptive Note:

Corporate Author:

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON D C

Report Date:

1961-06-01

Pagination or Media Count:

61.0

Abstract:

An investigation was conducted to determine the performance and flow separation characteristics of a family of conical rocket exhaust nozzles. The nozzles were mounted on a water-cooled JP-4 gaseous-oxygen thrust chamber with a 2.67-inchdiameter throat. The range of nozzle variables included divergent half-angles from 15 to 30 degrees nozzle area ratios from 81 to 751, and pressure ratios from 35 to 840. The results of the investigation showed that, for nozzles of equal length, the 20 or 25 degrees half-angles were superior at vacuum conditions. The advantage of these over the smaller area ratio, 15 degrees half-angle nozzles amounted to about 1 in thrust coefficient. Nozzle separation characteristics were generalized by the use of the Mach number ratio across the oblique shock wave which occurs at the separation point. Author

Subject Categories:

Distribution Statement:

APPROVED FOR PUBLIC RELEASE