Investigations of tail buffet on the CF-18 were conducted at the National Aeronautical Establishment (NAE) and the Aerospace Engineering Test Establishment (AETE). Flow visualization of the vortex burst phenomenon was carried out in a low speed water tunnel using a modified 1/72 scaled plastic model. In wind tunnel tests, a rigid 6 percent model was used for measurements in the NAE 5 x 5 ft Trisonic Tunnel. Unsteady pressure measurements on the vertical fin were made by means of 24 fast response transducers on each surface. Results of the acceleration experienced by the fin are presented. The vortex flow structure was studied with the aid of a 49 pressure-sensor-rake mounted behind the fin. In addition to measuring steady pitot pressure values, to deduce pressure contours, unsteady pressure fluctuations were obtained from 13 fast response transducers. The leading edge extension (LEX) was also instrumented with pressure orifices and fast response transducers. The investigation was carried out with LEX fences on and off to note their effect on tail buffet loads. Flight tests were conducted at AETE on a test aircraft with accelerometers installed on the vertical fins and horizontal stabilators and strain gauges mounted on the aft fuselage structures and fin root attachment stubs. Flight test data are presented showing the effectiveness of the LEX fence in reducing aft fuselage structural response to buffet loads.
Wind Tunnel Investigation and Flight Tests of Tail Buffet on the CF-18 Aircraft
1990
26 pages
Report
No indication
English
Wind tunnel studies of F/A-18 tail buffet
AIAA | 1990
|Wind-tunnel studies of F/A-18 tail buffet
AIAA | 1992
|