| タイトル | Identification of Experimental Unsteady Aerodynamic Impulse Responses |
| 本文（外部サイト） | http://hdl.handle.net/2060/20040085765 |
| 著者（英） | Silva, Walter A.; Piatak, David J.; Scott, Robert C. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 2003-01-01 |
| 言語 | eng |
| 内容記述 | The identification of experimental unsteady aerodynamic impulse responses using the Oscillating Turntable (OTT) at NASA Langley's Transonic Dynamics Tunnel (TDT) is described. Results are presented for two configurations: a Rigid Semispan Model (RSM) and a rectangular wing with a supercritical airfoil section. Both models were used to acquire unsteady pressure data due to pitching oscillations on the OTT. A deconvolution scheme involving a step input in pitch and the resultant step response in pressure, for several pressure transducers, is used to identify the pressure impulse responses. The identified impulse responses are then used to predict the pressure response due to pitching oscillations at several frequencies. Comparisons with the experimental data are presented. |
| NASA分類 | Aerodynamics |
| レポートNO | AIAA Paper 2003-1959 |
| 権利 | Copyright, Distribution under U.S. Government purpose rights |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/88820 |
