The aim of this MCIP session was to discover the parallel CFD flow solver AVBP and to use it to simulate airfoil flows.
AVBP is a CFD code which has been developed at CERFACS. It solves compressible Navier-Stokes equations in 2D and 3D cases on structured,unstructured and hybrids meshes. This solver is particularly well adapted for combustion and internal aerodynamics problems and it is used by industrials in the field of motors conception for exemple.
In this study, we used AVBP for external aerodynamics flows on airfoils. It is not really its "speciality" (in particular the limit conditions are very different from an internal aerodynamics study) but it allows to obtain good results.
We worked on two airfoils: NACA12 and Airfoil A. In both cases, we calculates the pressure coefficient and then integrates it in order to determinate polars (lift coefficient as a function of incidence flow). The NACA12 is an airfoil made by the NASA, used mostly for supersonic flows so we run simulations with a Mach number of 1,2. Airfoil A is a theorical airfoil made by AEROSPATIALE in order to test some particular aspects of wings. We used it on subsonic conditions for a Mach number of 0,3.
For the NACA12 airfoil, we also tried to compare simulations made with different meshes.
For these two airfoils, we didn't have to mesh the geometry (because of the few number of sessions) and the pre-processing part was reduced to the modification of the input file run.dat of AVBP. Then, the simulations were made using mpi in order to run on several processors, and finaly the post-processing part consisted in first the visualization of the convergence plot with xmgr, then the visualization of the flow with dplot and finally the determination of the pressure distribution and the lift coefficient.