Performance of Small (100-lb Thrust) Rocket Motors Using Coaxial Injection of Hydrazine and Nitrogen Tetroxide.
Abstract
An investigation was conducted on a small (approximately 100-lb thrust) rocket using coaxial injection of N2H4 and N204. Characteristicvelocity efficiencies of 94% of the theoretical shifting equilibrium value were obtained at a chamber pressure of about 300 psi using a 21tube injector and a combustion chamber characteristic length of 10 inches. Performance at lower chamber pressures could be improved by reducing contraction ratio and thereby increasing the combustion chamber length and injector pressure drop, which would tend to promote better mixing. Calculations based on experimental data showed a vacuum specific impulse of 305 sec. with a nozzle area ratio of 50. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1961
- Accession Number
- AD0267306
Entities
People
- Joseph F. Wasserbauer
- William Tabata
Organizations
- National Aeronautics and Space Administration