| タイトル | Finite area combustor theoretical rocket performance |
| 本文（外部サイト） | http://hdl.handle.net/2060/19880011868 |
| 著者（英） | Gordon, Sanford; Mcbride, Bonnie J. |
| 著者所属（英） | NASA Lewis Research Center |
| 発行日 | 1988-04-01 |
| 言語 | eng |
| 内容記述 | 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. |
| NASA分類 | SPACECRAFT PROPULSION AND POWER |
| レポートNO | 88N21252
NAS 1.15:100785
NASA-TM-100785
E-3975 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/146664 |
