| タイトル | Fluctuating loads measured on an over-the-wing supersonic jet model |
| 本文（外部サイト） | http://hdl.handle.net/2060/19790008470 |
| 著者（英） | Willis, C. M. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 1979-01-01 |
| 言語 | eng |
| 内容記述 | Fluctuating pressure loads on the wing and flap of an over-the-wing supersonic jet model were measured. The model was tested statically and at a Mach number of 0.1 in a small free jet to simulate forward speed. Test parameters were impingement angle, nozzle height, and flap deflection. Load levels as high as 170 db were measured at the center of the impingement region during static tests. Forward speed reduced the loading about 1 db. Load level increased with increasing impingement angle and decreasing nozzle height above the wing. The effect of flap deflection was small. When scaled to full-size aircraft conditions, the maximum amplitude of the one-third-octave fluctuating pressure spectra was about 154 db at about 160 Hz. Maximum load level occurred near the intersection of the nozzle center line with the impinged surface. Downstream of the maximum the fluctuating pressure is inversely proportional to the distance downstream of the nozzle. |
| NASA分類 | ACOUSTICS |
| レポートNO | 79N16641
L-12511
NASA-TP-1366 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/176595 |
