Dataset for direct numerical simulations of a transonic airfoil at a Reynolds number of Re=500,000

Abstract

These three folders comprise datasets corresponding to figure 5, figure 6 and figure 8 in Zauner et al. (2018): M. Zauner, N. De Tullio and N. Sandham, "Direct numerical simulations of transonic flow around an airfoil at moderate Reynolds numbers." in the AIAA Journal, 2018. https://doi.org/10.2514/1.J057335 All simulations were carried out at a Mach number of M=0.7 and a Reynolds number of Re=500,000. Description of content: - Fig5: Average skin-friction coefficient and pressure coefficient as a function of axial chord position. - Fig6: Skin friction as a function of time and space for the reference solution (case C0), the simulation with a grid refined in the xy-plane (G1) and the simulation with the reference xy-plane refined in the spanwise direction (G2). - Fig8: Instantaneous lift coefficient and surface density as function of time. The surface density is recorded at 10%, 30%, 50%, 70% of the axial chord length and at the leading- as well as trailing edge. - Movie showing vorticity contours in red and blue, and strong pressure gradients in the background.

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