The effect of 8 MeV proton irradiation on n-3C-SiC epitaxial layers grown by sublimation on semi-insulating 4H-SiC substrates has been studied. Changes in sample parameters were recorded using the Hall-effect method and judged from photoluminescence spectra. It was found that the carrier removal rate (Vd) in 3C-SiC is ~100 cm⁻¹, which is close to Vd in 4H-SiC. Compared with 4H and 6H silicon carbide, no significant increase in the intensity of the so-called defect-related photoluminescence was observed. An assumption is made that radiation-induced compensation processes in 3C-SiC are affected by structural defects (twin boundaries), which are always present in epitaxial cubic silicon carbide layers grown on substrates of the hexagonal polytypes.

Analysis of the Application of Turbulence Models in the Calculation of Supersonic Gas Jet

The aim of the study is to give a common classification of gasdynamic discontinuities, shock-wave structures and shock-wave processes. We have considered the classification of gas-dynamic discontinuities, shock-wave processes, shock-wave structures, discontinuity interaction problems. We have considered different classification criteria: thermodynamic, cinematic, transiency, discontinuity direction, arriving and outgoing discontinuities. A comprehensive list of discontinuity interference problems is given, as well as classification of possible transformations and wave front reorganization up to the case of the problem two-dimensional transient definition.

The article explores flow behavior around thick airfoils at low Reynolds numbers and the potential application of energy methods to manipulate the flow field for increased lift and reduced drag. The study relies on a set of propulsion airfoils calculated using a combined approach of solving the inverse problem of aerodynamics and applying stochastic global optimization methods. The calculations consider the transition from laminar to turbulent flow regimes, which significantly affects lift and airfoil drag. The suitability of different turbulence models for airfoil modeling in low Reynolds numbers is discussed, and numerical simulation results determine the lift coefficient dependence on angle of attack and the optimal air flow rate taken from the airfoil surface for each angle of attack. The accuracy of different turbulence models is analyzed by comparing numerical simulation results to physical experiment data.

The research objects of this study are new principles of gas turbine and rocket engines working process organization, based on the oscillatory motion of shock and detonation waves. Purpose is to identify the state of level technology, describe the subject area, state the direction of research and formulate the main problems hindering the implementation of wave technology into mass production. The results presented in the study can be recommended for developers of aircraft engines, power and technological turbo-machinery

Supersonic flows of gas in the vicinity of the bottom region known as flows with sudden expansion have been considered. On the basis of extensive experimental studies, authors have proposed a complete classification of flow regimes: stationary, oscillating, and transient. Hysteresis of the regimes change at total gas pressure increasing and decreasing in front of the nozzle has been found. Typical shock-wave configurations emerging at the jet flowing in a channel at different modes have been determined. The type of shock-wave structure and the nature of interaction of the mixing layer of a jet with the wall or reverse flow flowing into the channel from ambient medium determine the appropriate mode. Combination of physical and numerical experiment with bottom pressure calculation according to the developed semi-empirical model have revealed new flow regimes that were not studied earlier.