Abstract
In previous studies on the 1-kW hydrazine arcjet, two types of electrostatic probe diagnostics were used at the nozzle exit plane to measure electron density ne, electron temperature Te, ion Mach number, plasma velocity ui, gas temperature Tg, and related quantities. All measurements were performed at 10 A and 50 mg/s propellant mass flow on a NASA Lewis Research Center design, at a specific power of P/m = 22.4 MJ/kg. Further results for these studies when P/m = 19.8 MJ/kg and P/m = 26.0 MJ/kg are presented.
Original language | English (US) |
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Pages (from-to) | 735-736 |
Number of pages | 2 |
Journal | Journal of Propulsion and Power |
Volume | 15 |
Issue number | 5 |
DOIs | |
State | Published - 1999 |
ASJC Scopus subject areas
- Aerospace Engineering
- Fuel Technology
- Mechanical Engineering
- Space and Planetary Science