| タイトル | Analysis of experimental results of the inlet for the NASA hypersonic research engine aerothermodynamic integration model |
| 本文（外部サイト） | http://hdl.handle.net/2060/19760019115 |
| 著者（英） | Andrews, E. H., Jr.; Mackley, E. A. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 1976-06-01 |
| 言語 | eng |
| 内容記述 | An aerodynamic engine inlet analysis was performed on the experimental results obtained at nominal Mach numbers of 5, 6, and 7 from the NASA Hypersonic Research Engine (HRE) Aerothermodynamic Integration Model (AIM). Incorporation on the AIM of the mixed-compression inlet design represented the final phase of an inlet development program of the HRE Project. The purpose of this analysis was to compare the AIM inlet experimental results with theoretical results. Experimental performance was based on measured surface pressures used in a one-dimensional force-momentum theorem. Results of the analysis indicate that surface static-pressure measurements agree reasonably well with theoretical predictions except in the regions where the theory predicts large pressure discontinuities. Experimental and theoretical results both based on the one-dimensional force-momentum theorem yielded inlet performance parameters as functions of Mach number that exhibited reasonable agreement. Previous predictions of inlet unstart that resulted from pressure disturbances created by fuel injection and combustion appeared to be pessimistic. |
| NASA分類 | AIRCRAFT PROPULSION AND POWER |
| レポートNO | 76N26203
L-10400
NASA-TM-X-3365 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/185496 |
