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Submission declined on 4 November 2023 by Stuartyeates (talk).
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Comment: Wikipedia articles require recent reliable independent secondary sources with in depth coverage of the subjects.If decent sources are added to the article, feel free to ping my talk page once you've resubmitted the article for review. Stuartyeates (talk) 21:33, 4 November 2023 (UTC)
Thrust coefficient or (sometimes ) is a dimensionless number that measures the performance of a nozzle, most commonly in a rocket engine, independent of combustion performance. It is often used to compare the performance of different nozzle geometries. After combining it with characteristic velocity , then an effective exhaust velocity and a specific impulse can be found to characterize the overall efficiency of a rocket engine design.[1]
The thrust coefficient characterizes the supersonic flow in the expansion section downstream of the nozzle throat, in contrast to characteristic velocity which characterizes the subsonic flow in the combustion chamber and contraction section upstream of the throat.[2]
- ^ Heister, Stephen D.; Anderson, William E.; Pourpoint, Timothée; Cassady, Joseph (2018). Rocket propulsion (First ed.). New York: Cambridge University Press. ISBN 978-1-108-42227-7.
- ^ Rao, G. V. R. (November 1961). "Recent Developments in Rocket Nozzle Configurations". ARS Journal. 31 (11): 1488–1494. doi:10.2514/8.5837. ISSN 1936-9972.
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