| タイトル | Subsonic/supersonic aerodynamic characteristics for a tactical supercruiser |
| 著者（英） | Hutchison, R.; Bare, E. A.; Hollenback, D.; Capone, F. J. |
| 著者所属（英） | Boeing Military Airplane Development; NASA Langley Research Center |
| 発行日 | 1984-08-01 |
| 言語 | eng |
| 内容記述 | A series of cooperative NASA-Langley/Boeing experimental investigations have been conducted to determine the aeropropulsive characteristics of an advanced tactical fighter designed for supersonic cruise. These investigations were conducted in the Langley 16-Foot Transonic and Lewis 10 x 10-Foot Supersonic Wind Tunnels at Mach numbers from 0.60 to 2.47. This fighter is a Mach 2.0, 49,000 pound class vehicle that features a close-coupled canard and underwing propulsion units that utilize multifunction two-dimensional exhaust nozzles. Tests were conducted to determine the basic aerodynamic characteristics of the configuration with flow-through nacelles in which the spillage effects of representative inlets were measured. The effects of thrust-induced forces on overall aerodynamic performance were evaluated with a series of multifunction nozzles installed on air-powered nacelles. An axisymmetric nozzle configuration was also tested to obtain comparative aeropropulsive performance. Trim aerodynamic characteristics for the flow-through and powered configurations and the effect of thrust vectoring at subsonic speeds are presented. |
| NASA分類 | AERODYNAMICS |
| レポートNO | 84A44195
AIAA PAPER 84-2192 |
| 権利 | Copyright |
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