Usage of Navier–Stokes–Fourier equations with artificial viscosity for calculation of the flow around sharp edge

Aim. The purpose of this work is to evaluate the results of a Navier–Stokes–Fourier model with an artificially introduced stagnation point to describe flow around a sharp edge at moderate supersonic Mach numbers.

Methodology. This paper utilizes the Navier–Stokes–Fourier equation system with artificial viscosity. The applied model features an artificially introduced stagnation point. A numerical method for solving these differential equations using an upwind scheme was used to implement the model.

Results. Calculated results for Mach numbers of 2 and 3 with different stagnation point coefficient beta in range from 0.1 to 0.2.

Research implications. The obtained results confirm the applicability of this model to calculating the density and normal stresses in flow around sharp edges. The model can be used to calculate the edges of nose cones of aircrafts, air intakes, and other similar surfaces of advanced aircraft in the fields of aerospace engineering.

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