THEORETICAL PERFORMANCE OF PROPELLANTS SUITABLE FOR ELECTROTHERMAL JET ENGINES
The performance of eight possible propellants for electrothermal jet engines is evaluated theoretically. Performance characteristics are presented for enthalpies up to 200,000 Btu/lb, temperatures as high as 45,000 f R, pressures ranging from 0.0l to l00 atm, and specific impulses from 500 to 2000 sec. Of the propellants studied, hydrogen and helium appear to be the best for specific impulse in the vicinity of 1000 sec. At specific impulses greater than 1600 sec, lithium becomes more efficient. (auth)
- Research Organization:
- NASA Lewis Research Center, Cleveland
- Sponsoring Organization:
- USDOE
- NSA Number:
- NSA-16-006248
- OSTI ID:
- 4804230
- Journal Information:
- ARS (Am. Rocket Soc.) J., Journal Name: ARS (Am. Rocket Soc.) J. Vol. Vol: 31
- Country of Publication:
- Country unknown/Code not available
- Language:
- English
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