  We present the implementation and validation of an immersed boundary volume
penalization method in the computational fluid dynamics solver CODA (from
ONERA, DLR, and Airbus). Our goal is to model and simulate turbulent fluid
flows in complex 3D aerodynamic configurations through the numerical solution
of the Reynolds--averaged Navier--Stokes equations using the Spalart--Allmaras
turbulent model. To do that, an immersed boundary method has been implemented
in CODA and an efficient preprocessing tool for the construction of
unstructured hexahedral meshes with adaptive mesh refinement around immersed
geometries has been developed. We report several numerical examples, including
subsonic and transonic flow past a NACA0012 airfoil, subsonic flow past an
MDA30P30N multi-element airfoil, and subsonic flow around the NASA high-lift
CRM aircraft. These simulations have been performed in the CODA solver with a
second-order finite volume scheme as spatial discretization and an implicit
backward Euler scheme based on the matrix-free GMRES block-Jacobi iterative
method. The reported numerical simulations are in very good agreement with
their corresponding experimental data. We conclude that the implemented
immersed boundary method is efficient, flexible, and accurate and can therefore
be used for aeronautical applications in industry.
