Meridional flow calculation methods (Turbomachinery) Inviscid Viscous N.-S.-like method flow reconstitution
	Blade-to-Blade calculation methods Inviscid N.-S. solver
	Inverse methods (2D and 3D Turbomachinery, afterbody, ducts, airfoils)
	3D Navier-Stokes solver (Turbomachinery, internal/external flow applications)

              The Research Group of LTT/NTUA has developed a number of computer codes using a finite difference/finite volume discretization and capable of solving inviscid and viscous flow problems in two and three dimensions. These codes have already been used and validated in a variety of realistic flow situations related to both external and internal aerodynamics, to steady and unsteady flows etc. It is worth noting that, since Turbomachinery is one of the main domains of interest, where very complex geometries and complicated flow patterns are present, LTT/NTUA solvers had to overcome quite a few practical difficulties before achieving a satisfactory state. In addition, some of these codes are implemented and used in the present moment in some of the established European Industries. These codes are being continuously improved by the LTT/NTUA staff. One of the approaches initially chosen in the Thermal Turbomachinery Lab, on both scientific and financial grounds consisted of finite difference/ finite volume techniques, using body-fitted structured grids . During the last two years, new activities in the field of finite-volume, primitive-variable solution methods unstructured grid Topologies have been initiated.