Abstract

Numerical and experimental investigations of the flow over a supercritical airfoil are performed at the Shock Wave Laboratory. The transonic airfoil flow contains complex structures such as local supersonic regions and local separation regions, shock-boundary layer interaction, vortex-wake interaction and boundary layer transition. Furthermore, a phenomenon of upstream moving waves is observed in the experiments as well as in the numerical simulations. This paper focus on the numerical investigation of the upstream moving wave phenomenon in the two-dimensional unsteady transonic airfoil flow. The influence of the Reynolds number, Mach number and the incidence on the mean and unsteady flow properties is analyzed. A direct eect of the Mach number and incidence is observed on the wave phenomenon, whereas the Reynolds number influences the time averaged flow field and hereby indirect the upstream moving waves.

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