| タイトル | Aerodynamic Characteristics of a Supersonic Fighter Aircraft Model at Mach 0.40 to 2.47 |
| 本文（外部サイト） | http://hdl.handle.net/2060/19860014090 |
| 著者（英） | Arbiter, D.; Capone, F. J.; Bare, E. A. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 1986-04-01 |
| 言語 | eng |
| 内容記述 | The aerodynamic characteristics of an advanced twin-engine fighter aircraft designed for supersonic cruise have been studied in the Langley 16-Foot Transonic Tunnel and the Lewis 10- by 10-Foot Supersonic Tunnel. The objective of this investigation was to establish an aerodynamic data base for the configuration with flow-through nacelles and representative inlets. The use of a canard for trim and the effects of fairing over the inlets were assessed. Comparisons between experimental and theoretical results were also made. The theoretical results were determined by using a potential vortex lift code for subsonic speeds and a linear aerodynamic code for supersonic speeds. This investigation was conducted at Mach numbers from 0.40 to 2.47, at angles of attack from 0 deg to about 20 deg, and at inlet capture ratios of about 0.5 to 1.4. |
| NASA分類 | AERODYNAMICS |
| レポートNO | 86N23561
NASA-TP-2580
NAS 1.60:2580
L-16017 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/65641 |
