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Sonic inlet noise attenuation and performance with a j-85 turbojet engine as a noise source
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Groth, H. W. |
| Copyright Year | 1974 |
| Description | A static test program was conducted to investigate aerodynamic and acoustic performance of a sonic inlet used as a noise suppressor. A translating centerbody type inlet with radial vanes was tested ahead of a J85-GE-13 turbojet engine. The inlet when fully choked, maintained high recovery with low distortions while dramatically reducing noise emanating from the compressor. Recoveries of 98.1% at simulated takeoff and 95% at approach were attained with associated sound attenuation of 40 db and 38 db respectively. Inlet lip shape was found to have significant effects on noise attenuation at these static conditions. |
| File Size | 972291 |
| Page Count | 14 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19740006271 |
| Archival Resource Key | ark:/13960/t7zm0405p |
| Language | English |
| Publisher Date | 1974-01-01 |
| Access Restriction | Open |
| Subject Keyword | Air Flow Acoustic Measurement Acoustic Properties Aerodynamic Configurations Engine Noise Noise Reduction Engine Inlets Inlet Flow Turbojet Engines Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
