| タイトル | A computational design tool for scramjet combustor film cooling and fuel mixing predictions |
| 著者（英） | Mcclinton, Charles R.; Kamath, Pradeep S.; Baker, N. R. |
| 著者所属（英） | NASA Langley Research Center; Analytical Services and Materials, Inc. |
| 発行日 | 1990-01-01 |
| 言語 | eng |
| 内容記述 | A methodology for the analysis of a film cooled combustor of a hydrogen-fueled, supersonic combustion ramjet (scramjet) is presented. The SHIP3D parabolic flow code, based on an extension of the pressure-correction method of Patankar and Spalding for compressible flow is used to compute the flow field in the combustor. The effect of film cooling on the overall vehicle performance is then calculated using the one-dimensional, multistep cycle code, CPIPE. Results are presented for a conceptual combustor at Mach 16 flight conditions. It is seen that film cooling can have a significant effect on the engine performance. |
| NASA分類 | AIRCRAFT PROPULSION AND POWER |
| レポートNO | 90A19964
AIAA PAPER 90-0645 |
| 権利 | Copyright |
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