Abstract
A computational aeroacoustics approach is applied to study sound propagation in subsonic and supersonic nozzle. The spatial derivatives are discretized by DRP scheme, and the low dissipation and dispersion Runge-Kutta scheme is used for time integration. The Giles' characteristic ID unsteady non-reflecting boundary conditions are applied to the inflow and outflow boundary regions. Numerical results agree well with analytical solutions and it reveals that the DRP scheme performs very well because of the high resolution and robust stability and is capable of calculating sound propagation.
| Original language | English |
|---|---|
| Pages (from-to) | 15-19 |
| Number of pages | 5 |
| Journal | Hangkong Dongli Xuebao/Journal of Aerospace Power |
| Volume | 18 |
| Issue number | 1 |
| State | Published - Feb 2003 |
Keywords
- Aerospace propulsion
- CAA
- High order scheme
- Non-reflecting boundary conditions
- Nozzle
- Sound propagation
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