| タイトル | Experimental study of three shock wave/turbulent boundary layer interactions |
| 著者（英） | Muck, Kin-Choong; Smits, Alexander J. |
| 著者所属（英） | Princeton Univ. |
| 発行日 | 1987-09-01 |
| 言語 | eng |
| 内容記述 | The paper presents a systematic study of the supersonic flow of a turbulent boundary layer over several compression-corner models. The wind tunnel and the compression-corner models (ramps fitted with aerodynamic fences to minimize three-dimensional effects) were identical with those used by Settles et al. (1979); constant-temperature hot-wire anemometry was used for the mass-flow measurements. The turning angles used for the compression corners were 8, 16, and 20 deg. In all three flow cases, the shock wave/turbulent flow interaction did amplify the turbulent stresses dramatically, with amplification increasing with increasing turning angle. However, different stress components were amplified by different amounts. |
| NASA分類 | AERODYNAMICS |
| レポートNO | 88A14461 |
| 権利 | Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/374213 |
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