| タイトル | Characterization of a hot-film probe for hypersonic flow |
| 著者（英） | Spina, E.; Mcginley, C.; Sheplak, M. |
| 著者所属（英） | NASA Langley Research Center; NASA Headquarters |
| 発行日 | 1995-01-01 |
| 言語 | eng |
| 内容記述 | The critical issues concerning the application of constant-temperature hot-film anemometry to hypersonic flow are reviewed and extended. Mass-flux static calibrations were conducted in a Mach 10 helium flow, while mass-flux and total-temperature static calibrations were made in a Mach 6 air flow. In addition, comparative hot-film/hot-wire turbulence measurements were made in a Mach 11 helium boundary layer to provide insight into the dynamic response of the hot film. The measurements indicate that substrate conduction 'losses' dominate the static response of the hot-film probe, thus resulting in poor sensitivity to mass-flux and total temperature. Furthermore, it has been found that it is not possible to isolate mass-flux fluctuations at high overheat ratios for the current hot-film design. Thus, the sapphire-substrate hot-film anemometer is a robust, high-bandwidth instrument limited to qualitative transition and turbulence measurements. Finally, the extension of this technique to providing quantitative information is dependent upon the development of lower thermal-conductivity substrate materials. |
| NASA分類 | AIRCRAFT PROPULSION AND POWER |
| レポートNO | 95A90440
AIAA PAPER 95-6110 |
| 権利 | Copyright |
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