| タイトル | Experimental study of acoustic loads on an upper-surface-blown STOL airplane configuration |
| 本文（外部サイト） | http://hdl.handle.net/2060/19800005623 |
| 著者（英） | Schoenster, J. A.; Willis, C. M. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 1979-12-01 |
| 言語 | eng |
| 内容記述 | Fluctuating pressure levels were measured on the flap and fuselage of an upper-surface-blown jet-flap airplane configuration in a wind tunnel. The model tested had turbofan engines with a bypass ratio of 3 and a thrust rating of 10 kN. Rectangular nozzles were mounted flush with the upper surface at 35 percent of the wing chord. Test parameters were flap deflection angle, jet impingement angle, angle of attack, free-stream velocity, spanwise location of the engine, and jet dynamic pressure. Load levels were high throughout the jet impingement region, with the highest levels (about 159 dB) occurring on the fuselage and near the knee of the flap. The magnitude of the forward-velocity effect appeared to depend upon the ratio of free-stream and jet velocities. Good agreement was obtained between fluctuating pressure spectra measured at jet dynamic pressures of 7 and 22 kPa when the spectra were scaled by nondimensional functions of dynamic pressure, velocity, and the empirical relationship between dynamic pressure and overall fluctuating pressure level. |
| NASA分類 | ACOUSTICS |
| レポートNO | 80N13879
NASA-TP-1577
L-13167 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/173918 |
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