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Effect of taper ratio on the low-speed rolling stability derivatives of swept and unswept wings of aspect ratio 2.61
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1951 |
| Description | Results of tests conducted in the 6-foot-diameter rolling-flow test section of the Langley stability tunnel to determine the effects of varying taper ratio on the rolling and static stability characteristics of a swept wing are presented; results are also given for the effects of varying taper ratio on an unswept wing and for the effects of sweep on a tapered wing. All the models were of aspect ratio 2.61 and had NACA 0012 sections normal to the quarter-chord line. Taper ratios of 1.00, 0.50, and 0.25 and sweep angles of 0 degrees and 45 degrees were investigated. |
| File Size | 7872020 |
| Page Count | 18 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19930083083 |
| Archival Resource Key | ark:/13960/t9k404f5t |
| Language | English |
| Publisher Date | 1951-11-01 |
| Access Restriction | Open |
| Subject Keyword | Wings, Complete - Sweep Stability, Static Damping Derivatives - Stability Wings, Complete - Taper AND Twist 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 |
