ANNULAR INTERNAL-EXTERNAL-EXPANSION ROCKET NOZZLES FOR LARGE BOOSTER APPLICATIONS
Abstract
Annular nozzles with area ratios of 15 and 25 with free-stream airflow through the center as well as around the outside of the exiting jet were investigated in quiescent air and at Mach 2 and 3. Over a pressure-ratio range of 40 to 1000, the ratio of actual to ideal thrust was constant at approximately 0.98. Compared with conventional convergent-divergent nozzles, the performance of the annular internal-external expansion nozzle for representative boost missions could yield significant orbital payload increases. A single flap on the external-expansion surface of the 25:1 annular nozzle produced a side force equal to 4% of the axial force with no measura le loss in axial thrust. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 01, 1961
- Accession Number
- AD0263082
Entities
People
- Glenn A. Mitchell
- James F. Connors
- Robert W. Cubbison
Organizations
- National Aeronautics and Space Administration