| タイトル | A nozzle internal performance prediction method |
| 本文（外部サイト） | http://hdl.handle.net/2060/19920024381 |
| 著者（英） | Carlson, John R. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 1992-10-01 |
| 言語 | eng |
| 内容記述 | A prediction method was written and incorporated into a three-dimensional Navier-Stokes code (PAB3D) for the calculation of nozzle internal performance. The following quantities are calculated: (1) discharge coefficient; (2) normal, side, and axial thrust ratios; (3) rolling, pitching, and yawing moments; and (4) effective pitch and yaw vector angles. Four different case studies are presented to confirm the applicability of the methodology. Internal and, in most situations, external flow-field regions are required to be modeled. The computed nozzle discharge coefficient matches both the level and the trend of the experimental data within quoted experimental data accuracy (0.5 percent). Moment and force ratios are generally within 1 to 2 percent of the absolute level of experimental data, with the trends of data matched accurately. |
| NASA分類 | AERODYNAMICS |
| レポートNO | 92N33625
NAS 1.60:3221
NASA-TP-3221
L-16965 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/126067 |
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