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Finite area combustor theoretical rocket performance
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Gordon, Sanford McBride, Bonnie J. |
| Copyright Year | 1988 |
| Description | Previous 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. |
| File Size | 690755 |
| Page Count | 20 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19880011868 |
| Archival Resource Key | ark:/13960/t6g20w819 |
| Language | English |
| Publisher Date | 1988-04-01 |
| Access Restriction | Open |
| Subject Keyword | Spacecraft Propulsion And Power Subroutines Iterative Solution Rocket Engines Adiabatic Conditions Mathematical Models Combustion Chambers Combustion Efficiency Propellant Combustion Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
