NACA0012 airfoil
The NACA0012 airfoil benchmark is one of the most classic and widely used test cases in computational fluid dynamics, especially for validating incompressible and compressible flow solvers, mesh adaptation, turbulence models, and fluid-structure interaction.
We reproduce case A5 from the GAMM Workshop. That is, a steady case with Re = 500, Ma = 0.85, and zero angle of attach.
The gas follows the perfect gas law, has a coefficient of specific heats of 1.4, and a Prandtl number of 0.72.
In particular we compare with Bristeau, how assigns the following boundary and initial conditions:
Computations are performed with the 2001 non diagonal compressible tau and the Hughes and Mallet 1998 discontinuity capturing, with a time step of 1e-3 s, a grid average size of 5e-3 m next to the airfoil, and 5e-2 far from it.
The specifications of fluid properties, initial and boundary conditions, setup of the stabilization parameters and time step, along with the definition of the mesh can be found if files props.txt, setup.txt, fluid_ic_bc.hpp, and mesh.geo.
The countours of density are compared with the reference case. The steady state is reached at about 30 s.
The pressure coefficients result as follows.
Reference
Numerical Simulation of Compressible Navier-Stokes Flows, A GAMM Workshop, Notes on Numerical Fluid Mechanics and Multidisciplinary Design, (2013)
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