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Record 1 of 5225
High-power hydrogen arcjet performance
Author and Affiliation:
Haag, Thomas W.(NASA Lewis Research Center, Cleveland, OH, United States)
Curran, Francis M.(NASA Lewis Research Center, Cleveland, OH, United States)
Abstract: A hydrogen arcjet was operated at power levels ranging from 5 to 30 kW with three different nozzle geometries. Test results using all three nozzle geometries are reported and include variations of specific impulse with flow rate, and thrust with power. Geometric variables investigated included constrictor diameter, length, and diverging exit angle. The nozzle with a constrictor diameter of 1.78 mm and divergence angle of 20 deg was found to give the highest performance. A specific impulse of 1460 s was attained with this nozzle at a thrust efficiency of 29.8 percent. The best efficiency measured was 34.4 percent at a specific impulse of 1045 s. Post test examination of the cathode showed erosion after 28 hours of operation to be small, and limited to the conical tip where steady state arc attachment occurred. Each nozzle was tested to destruction.
Publication Date: Jun 01, 1991
Document ID:
19910061172
(Acquired Nov 28, 1995)
Accession Number: 91A45795
Subject Category: SPACECRAFT PROPULSION AND POWER
Report/Patent Number: AIAA PAPER 91-2226
Document Type: Preprint
Publisher Information: United States
Financial Sponsor: NASA; United States
Organization Source: NASA Lewis Research Center; Cleveland, OH, United States
Description: 23p; In English
Distribution Limits: Unclassified; Publicly available; Unlimited
Rights: Copyright
NASA Terms: ARC JET ENGINES; HYDROGEN ENGINES; NOZZLE GEOMETRY; SPACECRAFT PROPULSION; SPECIFIC IMPULSE; ARC DISCHARGES; EROSIVE BURNING; FUEL FLOW; THRUST MEASUREMENT
Imprint And Other Notes: AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference, 27th, Sacramento, CA, June 24-26, 1991. 23 p.
Availability Source: Other Sources
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