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An evaluation of three helicopter rotor sections
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Collins, L. J. Hicks, R. M. |
| Copyright Year | 1985 |
| Description | Three helicopter rotor sections were tested in the NASA Ames Research Center 2- by 2-Foot Transonic Wind Tunnel over a Mach range from 0.2 to 0.88. The sections tested had maximum thickness/chord ratios of 0.078, 0.09, and 0.10. The thickest section was of early technology and had been tested previously in other wind tunnels. This section was included in the investigation to establish a basis for comparing the two thinner sections, which were of recent design. The results of the investigation showed that the pitching-moment characteristics for the three airfoil sections were acceptable. The drag divergence Mach numbers for the three sections were 0.80, 0.825, and 0.845 in order of decreasing thickness. |
| File Size | 9071889 |
| Page Count | 124 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19850025802 |
| Archival Resource Key | ark:/13960/t2r54hj37 |
| Language | English |
| Publisher Date | 1985-08-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Thickness Aerodynamic Drag Pitching Moments Helicopters Wind Tunnel Tests Airfoils Aerodynamic Coefficients Rotary Wings Mach Number Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
