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International audienceThis paper aims to present some of the experimental and numerical results obtained with the NASA–Boeing Common Research Model at ONERA. The wind tunnel model used in the present study is the ONERA Large Reference Model (1/16.835), which has the same geometry as the Common Resarch Model considered in the latest AIAA Drag Prediction Workshops. Experimental data have been collected from the ONERA-S1MA wind tunnel at Mach numbers between 0.30 and 0.95 and a mean aerodynamic chord Reynolds number of 5 million for four different configurations: wing/body only and wing/body with horizontal or vertical tails or both. Force and moment and pressure and surface flow measurements have been performed. Concerning the numerical study, all the Reynolds-averaged Navier–Stokes computations have been completed with the structured solver elsA, and the Spalart–Allmaras and kω with shear stress transport turbulence models have been used in addition to the quadratic constitutive relation. In this paper, configuration effects (increments due to horizontal and/or vertical tails) are assessed both numerically and experimentally for several Mach numbers and angles of attack. The delicate issue of flow separation at the wing/body junction is also addressed with the support of oil flow visualizations. elsA and S1MA skin pressure distributions are presented; the agreement is satisfactory except for some outboard wing sections at high lift levels. Finally, comparisons of drag and moment values including computational fluid dynamics and test data from different wind tunnels are proposed (S1MA, NASA Ames Research Center and National Transonic Facility, and European Transonic Wind Tunnel)

Experimental Investigations on Common Research Model at ONERA-S1MA–Drag Prediction Workshop Numerical Results