NASA NTRS · 19660044409
Flow system startup of a full-scale simulated nuclear rocket engine.
Abstract
Liquid hydrogen flow system performance during startup transient of nuclear rocket measured in full-scale simulated engine system, approximating in-flight exhaust conditions
Explore related subjects
Keep this discovery
Explore connections, maps & timelines
Colmery, B. H., Powers, A. G.. 1966-02-01. Flow system startup of a full-scale simulated nuclear rocket engine.. https://ntrs.nasa.gov/citations/19660044409
Cite the original work for its findings. Save a collection to share your selection of sources.