Development of Active Flutter Suppression Wind Tunnel Testing Technology
Final rept. Jun 1972-Sep 1974
BOEING WICHITA CO KS
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A research study was conducted to develop active flutter suppression wind tunnel testing technology. A one-thirtieth scale B-52 aeroelastic model was modified to represent the Control Configured Vehicles CCV B-52 flight test airplane with an active flutter mode control system FMCS. The system was mechanized on the model using electromechanical actuation systems for the scaled CCV airplane outboard aileron and flaperon outboard segment control surfaces. The model was tested in the NASA-Langley Transonic Dynamics Tunnel to evaluate the unaugmented model flutter characteristics and performance of the flutter mode control system. Test results were compared with model analytical results and CCV program flight test results for equivalent weight and altitude conditions. The model flutter speed, in airplane scale, is 8.1 percent higher than the airplane flutter speed, less than 1.0 percent higher than the predicted difference. Flutter mode damping with the FMCS engaged is higher on the model than on the airplane, but the damping trends with increasing airspeed are similar. The good agreement attained between model and airplane test results demonstrates that dynamically scaled models can be used to verify analytical methods used to design active flutter mode control systems.