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Application of finite difference techniques to noise propagation in jet engine ducts
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Baumeister, K. J. |
| Copyright Year | 1973 |
| Description | A finite difference formulation is presented for wave propagation in a rectangular two-dimensional duct without steady flow. The difference technique, which should be useful in the study of acoustically treated inlet and exhausts ducts used in turbofan engines, can readily handle acoustical flow field complications such as axial variations in wall impedance and cross section area. In the numerical analysis, the continuous acoustic field is lumped into a series of grid points in which the pressure and velocity at each grid point are separated into real and imaginary terms. An example calculation is also presented for the sound attenuation in a two-dimensional straight soft-walled suppressor. |
| File Size | 760242 |
| Page Count | 23 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19730017288 |
| Archival Resource Key | ark:/13960/t9b61bm4z |
| Language | English |
| Publisher Date | 1973-01-01 |
| Access Restriction | Open |
| Subject Keyword | Aircraft Noise Propagation Numerical Analysis Ducts Noise Reduction Finite Difference Theory Turbofan Engines Exhaust Systems Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
