Abstract
A summary of participants results for the coupled aero-structural simulation test case from the 6$^\mathrm{th}$ AIAA Computational Fluid Dynamics Drag Prediction Workshop (DPW-6) held in Washington, D.C., 16-17 June 2016, is presented. The test case focuses on a static aero-elastic simulation of NASA's Common Research Model civil transport aircraft in the wing-body configuration, i.e. without engines, pylons, and horizontal tail. Flow conditions include the design point lift coefficient \boldmath$C_L = 0.5\pm0.0001$ at cruise flight. Aero-elastic simulations are performed on the 'Medium' baseline grid, coupled to a computational structural analysis, using either an existing finite-element model or modal data. Experimental validation data for this test case is available from a wind-tunnel test campaign performed at the European Transonic Wind Tunnel in Cologne, Germany.
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