| タイトル | Hypersonic characteristics of an advanced aerospace plane at Mach 20.3 |
| 本文（外部サイト） | http://hdl.handle.net/2060/19860005775 |
| 著者（英） | Mccandless, R. S. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 1985-12-01 |
| 言語 | eng |
| 内容記述 | Wind-tunnel studies have been performed in the Langley Hypersonic Helium Tunnel Facility to obtain static longitudinal and lateral-directional aerodynamic characteristics of an advanced aerospace plane concept. The nominal test conditions are a Mach number of 20.3 and a Reynolds number of 6.8 x 10 to the 6th power per foot at angles of attack from 0 to 25 deg and angles of sideslip of -3 and 0 deg. Stability and control characteristics are obtained for several deflections of the elevators, elevons, and rudder. In addition, a modified canopy is examined. The results indicate that this vehicle is longitudinally stable at angles of attack near the maximum lift-drag ratio. Also, the vehicle is shown to be directionally unstable with positive dihedral effect. |
| NASA分類 | AERODYNAMICS |
| レポートNO | 86N15245
NAS 1.15:86435
NASA-TM-86435
L-15953 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/155071 |
