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Drag, lift and pitching moment were calculated for the tested aircraft sectioned into the fuselage and stabilizer. The analysis also covered the pressure distribution on the surface of this aircraft and on its symmetry plane. The values of the analysed forces and moments on individual parts of the stabilizer for the defined angles of attack were also obtained. The conducted analysis is a preliminary aerodynamic study of a new type of aircraft which is a combination of a gyroplane and a multi-rotor. The obtained results allow the assessment of the aerodynamic performance of the aircraft with a double tail stabilizer and constitute the basis for further optimisation studies.

In the fall 2016, GeantV went through a thorough community evaluation of the project status and of its strategy for sharing the R&D results with the LHC experiments and with the HEP simulation community in general. Following this discussion, GeantV has engaged onto an ambitious 2-year road-path aiming to deliver a beta version that has most of the final design and several performance features of the final product, partially integrated with some of the experiment's frameworks. The initial GeantV prototype has been updated to a vector-aware concurrent framework, which is able to deliver high-density floating-point computations for most of the performance-critical components such as propagation in field and physics models. Electromagnetic physics models were adapted for the specific GeantV requirements, aiming for the full demonstration of shower physics performance in the alpha release at the end of 2017. We have revisited and formalized GeantV user interfaces and helper protocols, allowing to: connect to user code, provide recipes to access efficiently MC truth and generate user data in a concurrent environment.

The paper presents the results of numerical tests of the aerodynamics of the Gyro-One unmanned autogyro model. The geometry of the research object was developed using reverse engineering and CAD software. The created solid model of the aircraft was entered into the Ansys Meshing to generate a mesh. The boundary conditions and turbulence model were defined with Ansys Fluent software. The calculated parameters include the aerodynamic forces and the pitching moment generated on individual elements calculated with the CFD method for the selected values of the angle of attack, the velocity and pressure distributions in the plane of symmetry, and the pressure distribution on the aircraft surface for the defined measurement points. The obtained results made it possible to analyse the flow around the research object and become an introduction to further research into a hybrid multi-rotor aircraft based on the autogyro design.

This article presents a method of strength analysis of the rotorcraft component which is the rotor hub of an unmanned helicopter with a MTOW up to 150 kg. The simulation takes into account two materials of which individual elements are made, i.e. steel and aluminum alloy. The load scheme and element support were defined, and numerical calculations were performed in the Ansys Workbench software. The simulation results were presented in the form of stress maps and were subjected to detailed analysis for individual elements. In the last stage, critical places in the assessment of the strength of the elements were indicated. On the basis of the performed strength analysis, the obtained results were individually interpreted for each of the tested elements depending on the adopted safety factors.

Experimental analysis of combustion in CI engines is difficult due to the very short duration of this process and the unfavourable thermodynamic conditions prevailing in the combustion chamber (high pressure and temperature). An alternative is to perform numerical calculations using the CFD method based on a defined combustion model. Such an approach was used in this paper to investigate the influence of different fuel injection configurations and different swirl ratio on selected parameters of the combustion process in the designed two -stroke opposed piston engine. The combustion chamber of the tested engine was formed of two movable surfaces of pistons. The AVL Fire software was used to perform the simulation. As a result of the calculations, the dependence of rate of heat release, burnt mass fraction, mean pressure in cylinder and heat transfer coefficient on defined calculation cases was obtained. In addition, a spatial distribution of the combustion stream of injected fuel was obtained. On the basis of the results obtained, conclusions regarding the impact of the fuel injection configuration and the swirl ratio on the obtained engine performance were presented.

Clostridium difficile is the cause of the nosocomial C. difficile infection (CDI). The conventional antibiotics used in CDI therapy are often unsuccessful, and recurrent infections may occur. Biofilm formation by C. difficile is associated with chronic or recurrent infections; biofilms may contribute to virulence and impaired antimicrobial efficacy. Manuka honey, derived from the Manuka tree ( Leptospermum scoparium ), is known to exhibit antimicrobial properties that are associated with its significant content of methylglyoxal, a natural antibiotic. The aim of the present study was to determine the antimicrobial effect of Manuka honey on clinical C. difficile strains belonging to four prominent polymerase chain reaction (PCR) ribotypes (RTs) (RT017, RT023, RT027 and RT046) and on their biofilm formation in vitro. Minimal inhibitory and bactericidal concentrations (MICs and MBCs, respectively) were determined using the broth dilution method. The biomass of the biofilm and the clearance of C. difficile biofilms by Manuka honey were determined using the crystal violet staining method. The MIC and MBC of Manuka honey for C. difficile strains were equal at 6.25% (v/v). PCR RT027 strains produced more biofilm in vitro than the other examined strains. Manuka honey effectively inhibited biofilm formation by C. difficile strains of different PCR RTs.

Stability is a key aspect for aircraft as it directly affects its flight balance and manoeuvre capabilities. This numerical research with Ansys Fluent investigates an airflow around a model of the designed gyrocopter - Aduster to examine its static longitudinal stability for the given ranges of horizontal stabilizer angles and angles of attack. Our calculations give certain aerodynamic forces and moments. The paper investigates drag, lift, a pitching moment at the given angles as well as gives the calculated coefficients of those forces and the pitching moment. The research results and the stability criterion enable us to analyse our gyrocopter's static longitudinal stability.

It is necessary to evaluate the performance of the main rotor in design stages of a rotorcraft to obtain the assumed lift force and low aerodynamic drag. This paper presents the CFD numerical analysis of the autorotating rotor under transient conditions. Auto-rotation is particularly important in the case of gyrocopters, while in the case of helicopters it is related to flight safety. The calculations allowed us to obtain aerodynamic forces and torque as a function of rotor azimuth for individual rotor blades. The analysis was performed for a rotor tilted by 15 degrees toward the airflow direction. A geometric model was created for the calculations and then a computational model was created in Ansys Fluent software. The k-ω SST model was adopted as the turbulence model which considers the turbulence kinetic energy and its unit dissipation. The obtained results are presented in a rotor and flow coordinate system.

The study investigates a thin-walled support platform for an unmanned aerial vehicle, i.e. aluminum beams connected by flat bars and angle irons. The construction is a kind of frame for a propulsion unit of the designed aircraft which is a combination of a multi-copter and a gyrocopter. This construction was tested for various load patterns to investigate the stresses and strains its profiles are connected. The load patterns correspond to different operation modes of the propulsion system, and the finite element method (FEM) and the SolidWorks software were used for the numerical calculations. The research was done for elastic operation of the individual components of the support platform. The analysis enabled to verify the state of stresses on the critical spots of the construction and to develop a construction for ground and flight tests to verify the correct operation of the propulsion control system and optimize its operation in different flight states.

The beams of fast runaway electrons (RE), which are often produced during tokamak discharges, are particularly dangerous and can induce serious damages of the vacuum vessel and internal components of the machine. The proper and fast diagnostics of RE beams is essential for controlling the discharge, e.g., by early mitigation of disruptions and potentially dangerous RE beams. The diagnostics of RE beams is usually based on measurements of the radiation emitted either by these electrons, or as a result of their interactions with plasma and/or vessel walls. Such a radiation is usually recorded by the means of probes placed outside the vacuum vessel. The method developed by our team is based on the probe located inside the vacuum vessel. The probe can be used to detect highly localized RE bunches and to determine their spatial and temporal characteristics. During last few years, the NCBJ team have developed and used the RE diagnostics based on the Cherenkov effect observed in diamond radiators coupled with fast photomultipliers. During the investigated discharges, the probe was inserted into the vacuum vessel, and its head was placed at the plasma edge, where fast RE are expected. A correlation between signals recorded using our probes and other diagnostics, e.g., hard x-ray signals, was also studied. In this paper, we present recent results of the RE measurements by means of Cherenkov probes, which were performed in the COMPASS and TCV tokamaks.