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Some fuel loss rate and weight estimates of an open-cycle gas-core nuclear rocket engine
NTRS Full-Text: Click to View  [PDF Size: 1.2 MB]
Author and Affiliation:
Ragsdale, R. G.(NASA Lewis Research Center, Cleveland, OH, United States)
Abstract: Engine thrust, specific impulse, and uranium loss rate effects on gaseous fueled nuclear rocket engine weight
Publication Date: Jan 01, 1970
Document ID:
19700016142
(Acquired Nov 22, 1995)
Accession Number: 70N25447
Subject Category: NUCLEAR ENGINEERING
Report/Patent Number: NASA-TM-X-52775
Document Type: Technical Report
Publisher Information: United States
Financial Sponsor: NASA; United States
Organization Source: NASA Lewis Research Center; Cleveland, OH, United States
Description: 10p; In English
Distribution Limits: Unclassified; Publicly available; Unlimited
Rights: No Copyright
NASA Terms: FLOW VELOCITY; NUCLEAR ROCKET ENGINES; SPECIFIC IMPULSE; THRUST; URANIUM; WEIGHT (MASS); HYDROGEN; NUCLEAR FUELS; PRESSURE; ROCKET ENGINE DESIGN
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