During recent cryodeposit tests with an 0.18-N thruster, the mass flux in the plume back field was measured for the first time for nitrogen, carbon dioxide, and a mixture of nitrogen, hydrogen, and ammonia at various inlet pressures. This mixture simulated gases that would be generated by a hydrazine plenum attitude propulsion system. The measurements furnish a base upon which to build a mathematical model of plume back flow that will be used in predicting the mass distribution in the boundary region of other plumes. The results are analyzed and compared with existing analytical predictions.
Small rocket exhaust plume data
01.07.1972
Sonstige
Keine Angabe
Englisch
Rocket exhaust plume phenomenology
TIBKAT | 2000
|Rocket exhaust plume dimensions
AIAA | 1969
|Plasma Rocket With Hybrid Exhaust Plume
NTRS | 1987
|