Abstract
A sharp immersed boundary computational aeroacoustic simulation approach for open-rotor direct noise predictions is presented. A specific feature of the finite-difference based immersed boundary method is that the stencil coefficients in the vicinity of the immersed boundary are determined in such a way that the stability of the numerical scheme is improved. The characteristics of this immersed boundary method are discussed for acoustic scattering and the treatment of moving boundaries, such as accounting for freshly cleared and dead cells, efficient geometry queries and efficient computation of irregular boundary stencils and point clouds in the vicinity of the immersed boundary. It is shown that the numerical error when considering moving boundary problems consistently scales with the order of accuracy of the boundary discretization. Finally, the method is applied to simulate the flow around a contra-rotating open rotor at take-off and cruise conditions where experimental data is available for comparison. Excellent agreement for the noise predictions of the contra-rotating open rotor system are obtained between the numerical simulations and the experimental noise measurement.
| Original language | English |
|---|---|
| Pages (from-to) | 690-716 |
| Number of pages | 27 |
| Journal | Journal of Computational Physics |
| Volume | 388 |
| DOIs | |
| State | Published - Jul 1 2019 |
Bibliographical note
Funding Information:This work was supported by the NASA Advanced Air Transport Technology (AATT) project under the Advanced Air Vehicles Program (AAVP). The authors would like to thank the members of the experimental test team for access to the wind tunnel data and model geometry. The authors would also like to thank Dr. Edmane Envia and Dr. Christopher Miller of NASA Glenn Research Center, Dr. Jeffrey Housman of NASA Ames Research Center, and the acoustic working group team members at NASA Glenn and NASA Langley research center for many fruitful discussions on modeling open rotor noise. The authors are grateful for very detailed feedback provided by Dr. Jeffrey Housman and Dr. Joseph Kocheemoolayil through the NASA-ARC review process. The authors would also like to thank Timothy Sandstrom (BVH optimizations and Fig. 16 ) and Dr. Patrick Moran ( Fig. 21 ) of NASA Ames Research Center for their assistance. Computer time has been provided by the NASA Advanced Supercomputing (NAS) facility at NASA Ames Research Center.
Funding Information:
This work was supported by the NASA Advanced Air Transport Technology (AATT) project under the Advanced Air Vehicles Program (AAVP). The authors would like to thank the members of the experimental test team for access to the wind tunnel data and model geometry. The authors would also like to thank Dr. Edmane Envia and Dr. Christopher Miller of NASA Glenn Research Center, Dr. Jeffrey Housman of NASA Ames Research Center, and the acoustic working group team members at NASA Glenn and NASA Langley research center for many fruitful discussions on modeling open rotor noise. The authors are grateful for very detailed feedback provided by Dr. Jeffrey Housman and Dr. Joseph Kocheemoolayil through the NASA-ARC review process. The authors would also like to thank Timothy Sandstrom (BVH optimizations and Fig. 16) and Dr. Patrick Moran (Fig. 21) of NASA Ames Research Center for their assistance. Computer time has been provided by the NASA Advanced Supercomputing (NAS) facility at NASA Ames Research Center.
Publisher Copyright:
© 2019 Elsevier Inc.
Keywords
- Acoustic scattering
- Computational aero-acoustics
- Higher-order finite differences
- Immersed boundary method
- Moving boundary
- Rotor noise
ASJC Scopus subject areas
- Numerical Analysis
- Modeling and Simulation
- Physics and Astronomy (miscellaneous)
- Physics and Astronomy (all)
- Computer Science Applications
- Computational Mathematics
- Applied Mathematics