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Full-scale wind-tunnel studies of f/a-18 tail buffet
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | James, Kevin D. Meyn, Larry A. |
| Copyright Year | 1996 |
| Description | Tail buffet studies were conducted on a full-scale, production F/A-18 fighter aircraft in the 80 by 120 ft Wind Tunnel at NASA Ames Research Center. The F/A-18 was tested over an angle-of-attack range of 18-50 deg, and at wind speeds of up to 168 ft/s, corresponding to a Reynolds number of 12.3x10(exp 6) based on mean aerodynamic chord and a Mach number of 0.15. The port, vertical tail fin was instrumented and the aircraft was equipped with a removable leading-edge extension (LEX) fence. Time-averaged, power-spectral analysis results are presented for the tail fin bending moment derived from the integrated pressure field, for the zero side-slip condition, both with and without the LEX fence. The LEX fence significantly reduces the magnitude of the rms pressures and bending moments. Scaling issues are addressed by comparing full-scale results for pressures at the 60%-span and 45%-chord location with small-scale, F/A-18 tail-buffet data. The comparison shows that the tail buffet frequency scales very well with length and velocity. Root-mean-square pressures and power spectra do not scale as well. The LEX fence is shown to reduce tail buffet loads at all model scales. |
| File Size | 583366 |
| Page Count | 8 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_20010062623 |
| Archival Resource Key | ark:/13960/t51g5mx4p |
| Language | English |
| Publisher Date | 1996-05-01 |
| Access Restriction | Open |
| Subject Keyword | Aircraft Stability And Control Tail Assemblies Bending Moments Wind Tunnel Tests Wind Velocity Fins F-18 Aircraft Angle of Attack Buffeting Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
