| タイトル | Wind tunnel and analytical investigation of over-the-wing propulsion/air frame interferences for a short-haul aircraft at Mach numbers from 0.6 to 0.78 |
| 本文（外部サイト） | http://hdl.handle.net/2060/19770026170 |
| 著者（英） | Sewell, A. E.; Welge, H. R.; Wells, O. D.; Lopez, M. L.; Henne, P. A. |
| 著者所属（英） | Douglas Aircraft Co., Inc. |
| 発行日 | 1977-09-01 |
| 言語 | eng |
| 内容記述 | Results of analytical calculations and wind tunnel tests at cruise speeds of a representative four engine short haul aircraft employing upper surface blowing (USB) with a supercritical wing are discussed. Wind tunnel tests covered a range of Mach number M from 0.6 to 0.78. Tests explored the use of three USB nozzle configurations. Results are shown for the isolated wing body and for each of the three nozzle types installed. Experimental results indicate that a low angle nacelle and streamline contoured nacelle yielded the same interference drag at the design Mach number. A high angle powered lift nacelle had higher interference drag primarily because of nacelle boattail low pressures and flow separation. Results of varying the spacing between the nacelles and the use of trailing edge flap deflections, wing upper surface contouring, and a convergent-divergent nozzle to reduce potential adverse jet effects were also discussed. Analytical comparisons with experimental data, made for selected cases, indicate favorable agreement. |
| NASA分類 | AERODYNAMICS |
| レポートNO | 77N33114
MDC-J7601
NASA-CR-2905 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/181130 |
