WIND TUNNEL TESTS OF FULL-SCALE F/A-18 TWIN TAIL BUFFET: A SUMMARY OF PRESSURE AND RESPONSE MEASUREMENTS

摘要

Tail buffet tests were performed on a full-scale, production model F/A-18 in the 80-by-120 Foot Wind Tunnel at NASA Ames Research Center. Steady and unsteady pressures were recorded on both sides of the starboard vertical fin, along with starboard and port fin-tip accelerations. The test matrix included an angle-of-attack range of 20° to 40° a sideslip range of -16° to 16° and freestream speeds up to 100 knots. The maximum speed corresponds to a Reynolds number of 1.23~*10~7 based on the mean aerodynamic chord and a Mach number of 0.15. The aircraft was equipped with removable leading edge extension (LEX) fences that are used in flight to reduce tail buffet loads. Steady and unsteady pressures are presented for selected test cases, along with steady and unsteady root bending moments. Representative pressure, root bending moment, and acceleration power spectra are also discussed, as are selected pressure cross-spectral pressure densities