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Comparison of measured and calculated helicopter rotor impulsive noise. [wind tunnel test data and prediction analysis techniques
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Johnson, W. Lee, A. |
| Copyright Year | 1978 |
| Description | The thickness noise theory is discussed. Two full-scale rotors were tested in a wind tunnel with several tips involving changes in chord, thickness, and sweep. Impulsive noise data reduction procedures used are described. The calculated and measured impulsive noise peak pressures as a function of advancing tip Mach number are compared, showing good correlation for all rotors considered. |
| File Size | 677870 |
| Page Count | 29 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19780012974 |
| Archival Resource Key | ark:/13960/t17m52w19 |
| Language | English |
| Publisher Date | 1978-03-01 |
| Access Restriction | Open |
| Subject Keyword | Acoustics Blade Tips Noise Reduction Aircraft Noise Wind Tunnel Tests Helicopter Performance Impulse Generators Noise Measurement Prediction Analysis Techniques Rotary Wings Sound Pressure Ntrs Nasa Technical Reports ServerĀ (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |