OPTIMENGA_AERO_ANALYSIS performs high-accuracy numerical analysis of viscous flow about complex aerodynamic configurations, including complete aircrafts. Numerical modeling is performed by solving the full Reynolds-averaged Navier-Stokes equations of viscous compressible flow. Flow simulations are performed in a wide range of flow conditions which include subsonic, transonic and supersonic regimes of flight.

The input to the OPTIMENGA_AERO_ANALYSIS consists of a numerical grid around the analyzed aerodynamic configuration, and a list of prescribed flight conditions and parameters of the numerical iterative process. The basic output consists of plot files with the flow-field solution which can be used for flow visualization, and of alphanumeric files which record basic data appearing in the course of computation.

The algorithm of OPTIMENGA_AERO_ANALYSIS represents an iterative process embedded with a specially developed Multi-grid framework. A default Multi-grid structure is provided which may be tuned by the user in accordance with a required accuracy of analysis and with specific flight conditions. To enhance the accuracy and convergence, continuation runs are allowed.

The computer resources requirements fit in well with standard modern parallel clusters which operate under LINUX (CentOS 5.3 or Red Hat 5.3) and PVM version 3.4.5 or higher.

The wall clock run times depend on the complexity of an analyzed aerodynamic configuration as well as on specified flight conditions and required level of accuracy. For a standard transonic wing, the run times are typically from 20 minutes to one hour on a cluster of 10-20 cores, while for a complete aircraft configuration, the time consumption and required computer resources may amount to12 hours on a cluster of 200-300 cores, with minimum memory requirement of 2G per core..