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An analytical investigation of the free-tip rotor for helicopters
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Stroub, R. H. |
| Copyright Year | 1982 |
| Description | A rotor configuration called the free-tip rotor was analytically investigated for its potential to improve helicopter forward-flight performance characteristics. This rotor differs from a conventional rotor only in the blade tip region. In this configuration, the tip is self-adjusting in pitch with respect to the rest of the blade, in accordance with a moment balance about its pitch axis. With this self-adjusting capability, the resulting pitch motion generates a more uniform airload distribution around the azimuth. Computer math models were used to compare performance characteristics of the free tip rotor with those of a conventional rotor operation at flight speeds from 130 to 160 knots. The results of this analysis indicate that the free-tip rotor improves cruise lift-drag ratio by at least 22%. |
| File Size | 1068692 |
| Page Count | 34 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19820010305 |
| Archival Resource Key | ark:/13960/t4nk8605k |
| Language | English |
| Publisher Date | 1982-02-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Pitching Moments Blade Tips Helicopters Wing Tips Rotary Wings Pitch Inclination Airspeed Flight Characteristics Aerodynamic Configurations Mathematical Models Cruising Flight Helicopter Performance Rotor Lift Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
