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Flight performance of a transonic turbine-driven propeller designed for minimum noise
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1959 |
| Description | Results are presented of a flight investigation to determine the aerodynamic characteristics of a transonic-type propeller. This propeller was designed for an advance ratio of 4.0 at a forward Mach number of 0.82 in an effort to limit the noise production. The measured efficiency of the propeller was 68 percent at the design Mach number of 0.82. This value compares with an efficiency as much as 15 percent higher with the same Mach number for a propeller designed for an optimum advance ratio of about 3.0. This penalty in efficiency must be considered in light of the resulting noise reduction. The noise under static and take-off conditions was measured to be 117.5 decibels, which represents a noise reduction of about 5 decibels (at 1,400 horsepower) compared with the advance-ratio-3 -design. |
| File Size | 872358 |
| Page Count | 24 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19980232084 |
| Archival Resource Key | ark:/13960/t6935k114 |
| Language | English |
| Publisher Date | 1959-05-01 |
| Access Restriction | Open |
| Subject Keyword | Acoustics Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
