EXPERIMENTAL STUDY OF EFFECTS OF GEOMETRIC VARIABLES ON PERFORMANCE OF CONICAL ROCKET-ENGINE EXHAUST NOZZLES
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 8/1 to 75/1, 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)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 1961
- Accession Number
- AD0258759
Entities
People
- Harry E. Bloomer
- Paul E. Renas
- Rober J. Antl
Organizations
- National Aeronautics and Space Administration