| タイトル | Experimental study of sharp and blunt nose streamwise corners at Mach 20 |
| 本文（外部サイト） | http://hdl.handle.net/2060/19740011794 |
| 著者（英） | Watson, R. D. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 1974-04-01 |
| 言語 | eng |
| 内容記述 | Extensive heat transfer and pressure distribution data and oil flow studies on sharp and blunt-nose streamwise corners at Mach 20 in helium are presented. The far corner boundary layers on the wedge surfaces forming the corners are laminar for most test conditions. Analysis of the data indicates that the corner flow field geometry can be described in terms of the inviscid shock pattern on the two dimensional surfaces forming the corner. Parameters used to correlate blunt shock growth can be used to correlate features of the flow field observed in oil flow photographs in addition to the measured pressure and heat transfer distributions on the models. The flow field structure is described from available experimental data. Regions of the flow in which the structure still is not known are discussed. |
| NASA分類 | FLUID MECHANICS |
| レポートNO | 74N19907
NASA-TN-D-7398
L-8830 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/195311 |
