| タイトル | Experimental cavity pressure distributions at supersonic speeds |
| 本文（外部サイト） | http://hdl.handle.net/2060/19870013193 |
| 著者（英） | Stallings, Robert L., Jr.; Wilcox, Floyd J., Jr. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 1987-06-01 |
| 言語 | eng |
| 内容記述 | An investigation was conducted to define pressure distributions for rectangular cavities over a range of free-stream Mach numbers and cavity dimensions. These pressure distributions together with schlieren photographs are used to define the critical values of cavity length-to-depth ratio that separate open type cavity flows from closed type cavity flows. For closed type cavity flow, the shear layer expands over the cavity leading edge and impinges on the cavity floor, whereas for open type cavity flow, the shear layer bridges the cavity. The tests were conducted by using a flat-plate model permitting the cavity length to be remotely varied from 0.5 to 12 in. Cavity depths and widths were varied from 0.5 to 2.5 in. The flat-plate boundary layer approaching the cavity was turbulent and had a thickness of approximately 0.2 in. at the cavity front face for the range of test Mach numbers from 1.5 to 2.86. Presented are a discussion of the results and a complete tabulation of the experimental data. |
| NASA分類 | AERODYNAMICS |
| レポートNO | 87N22626
NASA-TP-2683
NAS 1.60:2683
L-16215 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/150748 |
