| タイトル | Aerodynamic characteristics of an NASA supercritical-wing research airplane model with and without fuselage area-rule additions at Mach 0.25 to 1.00 |
| 本文（外部サイト） | http://hdl.handle.net/2060/19780016137 |
| 著者（英） | Bartlett, D. W.; Harris, C. D. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 1972-12-01 |
| 言語 | eng |
| 内容記述 | Transonic pressure tunnel tests at Mach numbers from 0.25 to 1.00 were performed to determine the effects of area-rule additions to the sides of the fuselage on the aerodynamic characteristics of a 0.087 scale model of an NASA supercritical-wing research airplane. Presented are the longitudinal aerodynamic force and moment characteristics for horizontal-tail deflection angles of -2.5 deg and -5 deg with the side fuselage area-rule additions on and off the model. The effects of the side fuselage area-rule additions on selected wing and fuselage pressure distributions at near-cruise conditions are also presented. |
| NASA分類 | AERODYNAMICS |
| レポートNO | 78N24080
L-8422
NASA-TM-X-2633 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/178888 |
