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Wing-tip vanes as vortex attenuation and induced drag reduction devices
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Nagati, M. G. Wentz Jr., W. H. |
| Copyright Year | 1975 |
| Description | Analytical studies have been conducted to examine the feasibility of utilizing wing tip turbines to remove swirl from the wing trailing vortex, and hence reduce the potential for upset of following aircraft. Energy recovery from the turbines is also analyzed. A computer routine has been developed to permit rapid parametric studies of various tip turbine designs. It is shown that the optimum turbine is a non-rotating set of vanes which reduce swirl and recover energy in the form of reduced overall configuration induced drag. A specific case study indicates a 23% reduction in induced drag for a rectangular wing of aspect ratio 5.33, operated at a lift coefficient at 1.0. |
| File Size | 281786 |
| Page Count | 12 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19760003924 |
| Archival Resource Key | ark:/13960/t3615t53b |
| Language | English |
| Publisher Date | 1975-01-01 |
| Access Restriction | Open |
| Subject Keyword | Aircraft Design, Testing And Performance Turbine Blades Drag Reduction Rectangular Wings Vanes Wing Tips Vortex Breakdown General Aviation Aircraft Induced Drag Computer Aided Design Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
