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Finite area combustor theoretical rocket performancePrevious to this report, the computer program of NASA SP-273 and NASA TM-86885 was capable of calculating theoretical rocket performance based only on the assumption of an infinite area combustion chamber (IAC). An option was added to this program which now also permits the calculation of rocket performance based on the assumption of a finite area combustion chamber (FAC). In the FAC model, the combustion process in the cylindrical chamber is assumed to be adiabatic, but nonisentropic. This results in a stagnation pressure drop from the injector face to the end of the chamber and a lower calculated performance for the FAC model than the IAC model.
Document ID
Document Type
Technical Memorandum (TM)
Gordon, Sanford
(Gordon, Sanford, Cleveland Ohio , United States)
Mcbride, Bonnie J.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 5, 2013
Publication Date
April 1, 1988
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
NAS 1.15:100785
Accession Number
Funding Number(s)
PROJECT: RTOP 506-42-21
Distribution Limits
Work of the US Gov. Public Use Permitted.
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