An 18 percent aeroelastically-scaled, full span F/A-18 E/F model was tested during multiple wind-tunnel entries in the Langley Transonic Dynamics Tunnel. The primary purpose of these entries was to assist in clearing the flight vehicle design of flutter within its operating envelope. The wind-tunnel model was tested on a string and on a cable- mount system The model is shown on the cable-mount system with Langley engineer, Stanley Cole, checking tension in one of the support cables. All lifting surfaces were flutter cleared up to M=1.2 with the model string mounted. The model was then flutter cleared on the cable- mount system to assess the influence of rigid-body dynamics and fuselage flexibility on flutter. Several configuration parametric studies were also completed, including many external store configurations.
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