| タイトル | Numerical simulation of the edge tone phenomenon |
| 本文（外部サイト） | http://hdl.handle.net/2060/19940029392 |
| 著者（英） | Dougherty, N. S.; Liu, B. L.; Ofarrell, J. M. |
| 著者所属（英） | Rockwell International Corp. |
| 発行日 | 1994-02-01 |
| 言語 | eng |
| 内容記述 | Time accurate Navier-Stokes computations were performed to study a class 2 (acoustic) whistle, the edge tone, and to gain knowledge of the vortex-acoustic coupling mechanisms driving production of these tones. Results were obtained by solving the full Navier-Stokes equations for laminar compressible air flow of a two dimensional jet issuing from a slit interacting with a wedge. Cases considered were determined by varying the distance from the slit to the wedge. Flow speed was kept constant at 1,750 cm/s as was the slit thickness of 0.1 cm, corresponding to conditions in the experiments of Brown. The analytical computations revealed edge tones to be present in four harmonic stages of jet flow instability over the wedge as the jet length was varied from 0.3 to 1.6 cm. Excellent agreement was obtained in all four edge tone stage cases between the present computational results and the experimentally obtained frequencies and flow visualization results of Brown. Specific edge tone generation phenomena and further confirmation of certain theories and empirical formulas concerning these phenomena were brought to light in this analytical simulation of edge tones. |
| NASA分類 | AERODYNAMICS |
| レポートNO | 94N33898
NASA-CR-4581
M-744
NAS 1.26:4581 |
| 権利 | No Copyright |
|
