| タイトル | Pressure distributions obtained on a 0.10-scale model of the space shuttle Orbiter's forebody in the AEDC 16T propulsion wind tunnel |
| 本文（外部サイト） | http://hdl.handle.net/2060/19860009862 |
| 著者（英） | Siemers, P. M., III; Henry, M. W. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 1986-01-01 |
| 言語 | eng |
| 内容記述 | Pressure distribution test data obtained on a 0.10-scale model of the forward fuselage of the Space Shuttle Orbiter are presented without analysis. The tests were completed in the AEDC 16T Propulsion Wind Tunnel. The 0.10-scale model was tested at angles of attack from -2 deg to 18 deg and angles of side slip from -6 to 6 deg at Mach numbers from 0.25 to 1/5 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 orifices, the wind-tunnel model was also instrumented with orifices to match Development Flight Instrumentation (DFI) port locations that existed on the Space Shuttle Orbiter Columbia (OV-102) during the Orbiter Flight Test program. This DFI simulation has provided a means of comparisons between reentry flight pressure data and wind-tunnel and computational data. |
| NASA分類 | ASTRONAUTICS (GENERAL) |
| レポートNO | 86N19333
NASA-TM-87653
NAS 1.15:87653 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/154760 |
