| タイトル | Kinetic theory model predictions compared with low-thrust axisymmetric nozzle plume data |
| 本文（外部サイト） | http://hdl.handle.net/2060/19950024443 |
| 著者（英） | Fuhrman, S. J.; Penko, P. F.; Riley, B. R. |
| 著者所属（英） | NASA Lewis Research Center |
| 発行日 | 1993-01-01 |
| 言語 | eng |
| 内容記述 | A system of nonlinear integral equations equivalent to the steady-state Krook kinetic equation was used to model the flow from a low-thrust axisymmetric nozzle. The mathematical model was used to numerically calculate the number density, temperature, and velocity of a simple gas as it expands into a near vacuum. With these quantities the gas pressure and flow directions of the gas near the exit plane were calculated and compared with experimental values for a low-thrust nozzle of the same geometry and mass flow rate. |
| NASA分類 | SPACECRAFT PROPULSION AND POWER |
| レポートNO | 95N30864
NASA-CR-198934
NAS 1.26:198934 |
| 権利 | No Copyright |
