| タイトル | Pressure distributions obtained on a 0.04-scale and 0.02-scale model of the Space Shuttle Orbiter's forward fuselage in the Langley continuous flow hypersonic tunnel |
| 本文（外部サイト） | http://hdl.handle.net/2060/19830021007 |
| 著者（英） | Siemers, P. M., III; Henry, M. W.; Bradley, P. F.; Flanagan, P. F. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 1983-03-01 |
| 言語 | eng |
| 内容記述 | Results from pressure distribution tests on 0.04-scale and 0.02-scale models of the forward fuselage of the Space Shuttle Orbiter are presented without analysis. The tests wre completed in the Langley Continuous Flow Hypersonic Tunnel (CFHT). The 0.04-scale model was tested at angles of attack from -5 deg to 45 deg and angles of sideslip from -3 deg to 3 deg. The 0.02-scale model was tested at angles of attack from -10 deg to 45 deg and angles of sideslip from -5 deg to 5 deg. The tests were conducted in support of the development of the Shuttle Entry Air Data System (SEADS). In addition to modeling the 20 SEADS pressure orifices, the wind-tunnel models were also instrumented with orifices to match Development Flight Instrumentation (DFI) port locations currently existing on the Space Shuttle Orbiter Columbia (OV-102). This DFI simulation has provided a means for comparisons between reentry flight pressure data and wind-tunnel data. |
| NASA分類 | ASTRONAUTICS (GENERAL) |
| レポートNO | 83N29278
NASA-TM-84630
NAS 1.15:84630 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/162128 |
