| タイトル | Unstructured adaptive mesh computations of rotorcraft high-speed impulsive noise |
| 本文（外部サイト） | http://hdl.handle.net/2060/19940019834 |
| 著者（英） | Garceau, Michael; Biswas, Rupak; Strawn, Roger |
| 著者所属（英） | Research Inst. for Advanced Computer Science |
| 発行日 | 1993-10-01 |
| 言語 | eng |
| 内容記述 | A new method is developed for modeling helicopter high-speed impulsive (HSI) noise. The aerodynamics and acoustics near the rotor blade tip are computed by solving the Euler equations on an unstructured grid. A stationary Kirchhoff surface integral is then used to propagate these acoustic signals to the far field. The near-field Euler solver uses a solution-adaptive grid scheme to improve the resolution of the acoustic signal. Grid points are locally added and/or deleted from the mesh at each adaptive step. An important part of this procedure is the choice of an appropriate error indicator. The error indicator is computed from the flow field solution and determines the regions for mesh coarsening and refinement. Computed results for HSI noise compare favorably with experimental data for three different hovering rotor cases. |
| NASA分類 | ACOUSTICS |
| レポートNO | 94N24307
NASA-CR-195090
NAS 1.26:195090
RIACS-TR-93-10
AIAA PAPER 93-4359 |
| 権利 | No Copyright |
