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.
Full-Scale Wind-Tunnel Studies of F/A-18 Tail Buffet
AIAA 11th Applied Aerodynamics Conference ; 1993 ; Monterey, CA, United States
Journal of Aircraft ; 33 , 3
1996-05-01
Miscellaneous
No indication
English
Full-Scale Wind-Tunnel Studies of F-A-18 Tail Buffet
Online Contents | 1996
|Full-scale wind-tunnel studies of F/A-18 tail buffet
AIAA | 1996
|Full-Scale Wind Tunnel Studies of F/A-18 Tail Buffet
NTRS | 1993
|Wind tunnel studies of F/A-18 tail buffet
AIAA | 1990
|Full-Scale Wind-Tunnel Pressure Measurements of an F-A-18 Tail During Buffet
Online Contents | 1996
|