| タイトル | HYPULSE combustor analysis |
| 本文（外部サイト） | http://hdl.handle.net/2060/19940020298 |
| 著者（英） | Rizkalla, O. F. |
| 著者所属（英） | General Applied Science Labs., Inc. |
| 発行日 | 1993-12-01 |
| 言語 | eng |
| 内容記述 | The analysis of selected data from tests of unit fuel injectors in a generic scramjet combustor model is presented. The tests were conducted in the NASA HYPULSE expansion tube at conditions typical of flight at Mach 13.5 and 17. The analysis used a three-stream tube method, with finite-rate chemistry, in which the fuel, test gas, and mixing/combustive streams were treated independently but with the same static pressure. Performance of three candidate fuel injectors is examined based on deduced mixing and combustion efficiencies. |
| NASA分類 | FLUID MECHANICS AND HEAT TRANSFER |
| レポートNO | 94N24771
NASA-CR-191579
TR-352
NAS 1.26:191579 |
| 権利 | No Copyright |
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