| タイトル | Scramjet combustor and nozzle computations |
| 著者（英） | Mcclinton, Charles R.; Kamath, Pradeep S. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 1992-01-01
1992 |
| 言語 | eng |
| 内容記述 | The SHIP3D PNS code is used to conduct a 3D parametric study of a scramjet combustor and nozzle configuration at flight Mach numbers of 8, 10, 12, 16, and 20. The study demonstrated the powerful computational strategy of using a highly efficient, modified PNS code and a nonkinetic chemistry model to analyze test data and conduct parametric studies of scramjet combustors and nozzles. The mixing efficiency was found to decrease by 0.2 when the flight Mach number increased from 8 to 12 and showed little change at higher Mach numbers. The protruding ramp injector generated an oblique shock that impinged on the cowl. Ramp-slot injection produced better mixing, both because of the interaction of this shock with the slot fuel, and because of better fuel distribution in the duct. The former effect was enhanced when the ramp angle was increased. Mixing was also enhanced when the ramp fuel injection angle and sweep angle were increased. |
| NASA分類 | AIRCRAFT PROPULSION AND POWER |
| レポートNO | 93A14243 |
| 権利 | Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/322302 |
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