An experimental investigation is conducted of the plume of a 1.5 kW hydrogen-fueled arcjet thruster. The velocity and translational temperature are measured by laser induced fluorescence of excited-state atomic hydrogen at a variety of locations and operating conditions. The peak velocity and temperature at the center of the exit plane of 14.7 km/s and 5000 K lead to a Mach number of 1.9. Evidence is presented which demonstrates the extent to which viscous forces dominate the flow, such as the exit plane Reynolds number of 18. Data taken in the plume suggest a transition from supersonic to subsonic flow via viscous dissipation. In addition, the results suggest that high tank pressures (0.4 to 1.5 Torr) limit the ability to simulate space environments for different portions of the plume.
Plume characteristics of an arcjet thruster
AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference and Exhibit ; 1993 ; Monterey, CA, United States
1993-06-01
Aufsatz (Konferenz)
Keine Angabe
Englisch
Plume characteristics of an arcjet thruster
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