The development of the unsteady wake of transport aircraft under stall conditions and its impact on the empennage are challenging to predict, and the flow physics is far from being understood. In the European Strategic Wind Tunnels Improved Research Potential project, time-resolved particle image velocimetry measurements on the separated wake of the NASA Common Research Model were performed in the cryogenic European Transonic Windtunnel for flight Reynolds number conditions supplemented by aerodynamic measurements for a great variety of inflow conditions. In the time-resolved particle image velocimetry measurements, both low-speed stall (M ∞ 0.25, Re 11.6∕17 million) and high-speed stall conditions (M ∞ 0.85, Re 19.8∕30 million) were considered and the frequency resolution was as high as 1 kHz, enabling a sufficient characterization of the turbulent wake spectrum. For selected high-and low-speed stall conditions, hybrid Reynolds-averaged Navier-Stokes/large-eddy simulations were performed. In the present paper, the numerical results are discussed and compared to the experiments and first evaluations of the particle image velocimetry data are presented. NomenclatureYoung modulus M ∞ = freestream Mach number q = dynamic pressure Re = Reynolds number based on the reference chord length S = wing reference area Sr = Strouhal number based on the reference chord length and freestream velocity t = time U = velocity U ∞ = freestream velocity x, y, z = Cartesian coordinates y = wall distance normalized by the viscous length scale α = angle of attack Δ = filter width in large-eddy simulations η = spanwise position normalized by the semispan of the wing ω = vorticity

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