| タイトル | Mach 6 experimental and theoretical stability and performance of a finned cylindrical body at angles of attack up to 65 deg |
| 本文（外部サイト） | http://hdl.handle.net/2060/19870003105 |
| 著者（英） | Hartman, E. R.; Johnston, P. J. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 1986-09-01 |
| 言語 | eng |
| 内容記述 | A theoretical and experimental investigation of the longitudinal and lateral-directional stability and control of a finned cylindrical body has been conducted at Mach 6. The angle-of-attack range extended from 20 to 65 deg. to encompass maximum lift. Stability, performance, and trim could be accurately predicted with the fins in the + arrangement but this was not the case when the fins were in the x orientation where windward fin choking occurred at angles of attack above 50 deg. reducing their effectiveness and causing pitch up. |
| NASA分類 | AERODYNAMICS |
| レポートNO | 87N12538
NAS 1.15:89050
NASA-TM-89050 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/152832 |
