The Aerodynamics and Design Group at MdT is
involved with research in applied aerodynamics and aircraft design.
The high level aim of the group is to carry out both experimental and computational research
that leads to enhanced understanding of, and improved measurement and numerical techniques for, industrially relevant aero flow
Current research projects include boundary layer control, development of computational algorithms for the design and analysis of aerospace vehicles, the study of differential diffusion in a turbulent jet, unsteady aerodynamic studies on wings and airfoils in subsonic and supersonic flows with applications to aero-elastic oscillations control, studies on the next-generation hypersonic air-breathing engines, computational and numerical investigations of compact heat exchangers, and the study wing tip vortices from fixed and cyclically pitched wings.
The Aerodynamics group have collaborative contracts with a few Ukrainian aerospace companies, and collaborative links with many international research institutes.
Numerical simulation is a tool to design aircraft (AC), nevertheless, at this moment to obtain reliable results
moves to the supersonic flow regimes, i.e. to the conditions of a significant
preponderance of the wave resistance of the viscous. In the deep subsonic region the situation
is less favorable due to incompleteness of the general theory of turbulence.
Counter Rotating Open Rotor (CROR)
Many successful strategies and numerical schemes have been developed for simulating time dependent geometries. Most of these have been aimed at the two principal difficulties met in the computations, namely, the tracking of time dependent boundaries and adequate mapping of the complex computational domain.
Our group has developed a sliding interface method for simulations
involving relative grid motion that is fast and efficient and involves no grid deformation, remeshing, or hole
cutting. The method is implemented into a parallel, node-centered finite volume, structured viscous flow solver.
The rotational motion is accomplished by rigidly rotating the subdomain representing the moving component.
At the subdomain interface boundary, the faces along the interface are extruded into the adjacent subdomain
to create new volume elements and forming a one-cell overlap. These new volume elements are
to be used to compute a flux across the subdomain interface. An interface flux is computed independently for
each subdomain. The values of the solution variables and other quantities for the nodes created
by the extrusion process are determined by linear interpolation.
The extrusion is done so that the interpolation will maintain information as localized as possible.
The grid on the interface surface is arbitrary. The boundary between the two subdomains is completely
independent from one another; meaning that they do not have to connect in a one-to-one manner and no symmetry
or pattern restrictions are placed on the grid. A variety of numerical simulations are performed
on model problems and large-scale applications to examine conservation of the interface flux.