A 1/6-scale F-18 wind-tunnel model was tested in the Transonic Dynamics Tunnel at the NASA Langley Research Center as part of the Actively Controlled Response Of Buffet-Affected Tails (ACROBAT) program to assess the use of active controls in reducing vertical tail buffeting. The starboard vertical tail was equipped with an active rudder and other aerodynamic devices, and the port vertical tail was equipped with piezoelectric actuators. The tunnel conditions were atmospheric air at a dynamic pressure of 14 psf. By using single-input-single-output control laws at gains well below the physical limits of the control effectors, the power spectral density of the root strains at the frequency of the first bending mode of the vertical tail was reduced by as much as 60 percent up to angles of attack of 37 degrees. Root mean square (RMS) values of root strain were reduced by as much as 19 percent. Stability margins indicate that a constant gain setting in the control law may be used throughout the range of angle of attack tested.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Active Vertical Tail Buffeting Alleviation on a Twin-Tail Fighter Configuration in a Wind Tunnel


    Contributors:
    R. W. Moses (author)

    Publication date :

    1997


    Size :

    8 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English





    Vertical tail buffeting of fighter aircraft

    Lee, B.H.K. | Online Contents | 2000


    VORTEX CONTROL FOR TAIL BUFFET ALLEVIATION ON A TWIN-TAIL FIGHTER CONFIGURATION

    Puram, C. K. / Rao, Dhanvada M. / Shah, Gautam H. | SAE Technical Papers | 1989



    Active Vertical Tail Buffeting Alleviation on an F/A-18 Model in a Wind Tunnel

    Moses, R. W. / United States; National Aeronautics and Space Administration / United States; Federal Aviation Administration et al. | British Library Conference Proceedings | 1999