This paper describes the experimental studies of a laboratory model of a low power arc-jet thruster. A 350 W-class radiation-cooled arcjet thruster with nitrogen as propellant was developed for the validation of numerical results of arcjet performance. The arc-jet thruster was operated using a nozzle with 1.0mm in constrictor diameter. Thrust and input power were measured for various arc currents and mass flow rates. Stable operation was obtained at the power levels from 200 W to 500 W and mass flow rates from 5 mg/sec to 30 mg/sec. Specific impulses of 140 seconds at 300 W and 180 seconds at 450 W were achieved. The experimental data were compared with the computations, and the discrepancy between experiments and computations is discussed.
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