Book Description

Results are presented which define unsteady flow conditions associated with the high-dynamic structural response of a high-aspect-ratio, elastic, supercritical wing at transonic speeds. The wing was tested in the Langley Transonic Dynamics Tunnel with a heavy gas test medium. The supercritical wing, designed for a cruise lift coefficient of 0.53 at a Mach number of 0.80, experienced the high-dynamic structural response from Mach 0.90 to 0.94 with the maximum response occurring at about Mach 0.92. At the maximum response conditions of the wing, the forcing function appears to be the oscillatory chordwise movement of strong shocks located on the upper and lower surfaces of the wing in conjunction with the flow separation on the lower surface of the wing in the trailing-edge cove region. Eckstrom, Clinton V. and Seidel, David A. and Sandford, Maynard C. Langley Research Center AEROELASTICITY; DYNAMIC RESPONSE; PRESSURE DISTRIBUTION; SUPERCRITICAL WINGS; TRANSONIC SPEED; UNSTEADY FLOW; WIND TUNNEL TESTS; AERODYNAMIC COEFFICIENTS; BOUNDARY LAYER SEPARATION; SEPARATED FLOW; SLENDER WINGS; TRAILING EDGES; TRANSONIC WIND TUNNELS...