| タイトル | Analysis of a Rocket Based Combined Cycle Engine during Rocket Only Operation |
| 本文（外部サイト） | http://hdl.handle.net/2060/19980237203 |
| 著者（英） | Steffen, C. J., Jr.; Smith, T. D.; Yungster, S.; Keller, D. J. |
| 著者所属（英） | NASA Lewis Research Center |
| 発行日 | 1998-10-01 |
| 言語 | eng |
| 内容記述 | The all rocket mode of operation is a critical factor in the overall performance of a rocket based combined cycle (RBCC) vehicle. However, outside of performing experiments or a full three dimensional analysis, there are no first order parametric models to estimate performance. As a result, an axisymmetric RBCC engine was used to analytically determine specific impulse efficiency values based upon both full flow and gas generator configurations. Design of experiments methodology was used to construct a test matrix and statistical regression analysis was used to build parametric models. The main parameters investigated in this study were: rocket chamber pressure, rocket exit area ratio, percent of injected secondary flow, mixer-ejector inlet area, mixer-ejector area ratio, and mixer-ejector length-to-inject diameter ratio. A perfect gas computational fluid dynamics analysis was performed to obtain values of vacuum specific impulse. Statistical regression analysis was performed based on both full flow and gas generator engine cycles. Results were also found to be dependent upon the entire cycle assumptions. The statistical regression analysis determined that there were five significant linear effects, six interactions, and one second-order effect. Two parametric models were created to provide performance assessments of an RBCC engine in the all rocket mode of operation. |
| NASA分類 | Spacecraft Propulsion and Power |
| レポートNO | NASA/TM-1998-206639/REV1
NAS 1.15:206639/REV1
E-11106 |
| 権利 | No Copyright |
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