Sound Generation Mechanism of Shock-Associated Noise
Author:
Affiliation:
1. Rose-Hulman Institute of Technology
2. Stanford University
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.2003-3315
Reference14 articles.
1. Boundary conditions for direct computation of aerodynamic sound generation
2. Low-Dissipation and Low-Dispersion Runge–Kutta Schemes for Computational Acoustics
3. Compact finite difference schemes with spectral-like resolution
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