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A survey of the broadband shock associated noise prediction methods
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Krejsa, Eugene A. Kim, Chan M. Khavaran Sr., Abbas |
| Copyright Year | 1992 |
| Description | Several different prediction methods to estimate the broadband shock associated noise of a supersonic jet are introduced and compared with experimental data at various test conditions. The nozzle geometries considered for comparison include a convergent and a convergent-divergent nozzle, both axisymmetric. Capabilities and limitations of prediction methods in incorporating the two nozzle geometries, flight effect, and temperature effect are discussed. Predicted noise field shows the best agreement for a convergent nozzle geometry under static conditions. Predicted results for nozzles in flight show larger discrepancies from data and more dependable flight data are required for further comparison. Qualitative effects of jet temperature, as observed in experiment, are reproduced in predicted results. |
| File Size | 1072240 |
| Page Count | 28 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19920005579 |
| Archival Resource Key | ark:/13960/t2h75b91z |
| Language | English |
| Publisher Date | 1992-01-01 |
| Access Restriction | Open |
| Subject Keyword | Acoustics Acoustic Measurement Jet Aircraft Noise Broadband Engine Noise Convergent-divergent Nozzles Convergent Nozzles Nozzle Geometry Shock Waves Supersonic Aircraft Temperature Effects Noise Prediction Aircraft Supersonic Jet Flow Prediction Analysis Techniques Aeroacoustics Noise Prediction Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
