An investigation was conducted on a small (approximately 100-lb thrust) rocket using coaxial injection of hydrazine and nitrogen tetroxide. Characteristic-velocity efficiencies of 94 percent of the theoretical shifting equilibrium value were obtained at a chamber pressure of about 300 pounds per square inch using a 21-tube 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 seconds with a nozzle area ratio of 50.
Performance of Small (100-lb Thrust) Rocket Motors Using Coaxial Injection of Hydrazine and Nitrogen Tetroxide
1961
28 pages
Report
No indication
English
Numerical Study of Hydrazine and Nitrogen Tetroxide Combustion in small Rocket Motors
British Library Conference Proceedings | 1994
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