With the age of hypersonic flight imminent just beyond the horizon, researchers are working hard at designing work-arounds for all the major problems as well as the minor quirks associated with it. One such issue, seemingly innocuous but one that could be potentially deadly, is the problem of interference heating due to surface protuberances. Although an ideal design of the external surfaces of a high-speed aircraft dictates complete smoothness to reduce drag, this is not always possible in reality. Control surfaces, sheet joints, cable protection pads etc. generate surface discontinuities of varying geometries, in the form of both protrusions as well as cavities. These discontinuities are most often small in dimension, comparable to the local boundary layer thickness at that location. Such protuberances always experience high rates of heat transfer, and therefore should be appropriately shielded. However, thermal shielding of the protrusions alone is not a full solution to the problem at hand. The interference caused to the boundary layer by the flow causes the generation of local hot spots in the vicinity of the protuberances, which should be properly mapped and adequately addressed. The work presented in this thesis aims at locating and measuring the heat flux values at these hot spots near the protrusions, and possibly formulating empirical correlations to predict the hot spot heat flux for a given set of flow conditions and protrusion geometry. Experimental investigations were conducted on a flat plate model and a cone model, with interchangeable sharp and blunt nose tips, with attached 3D protuberances. Platinum thin-film sensors were placed around the protrusion so that the heat fluxes could be measured in its vicinity and the hottest spot located. These experiments were carried out at five different hypersonic free stream flow conditions generated using two shock tunnels, one of the conventional type, and the other of the free-piston driven type. The geometry of the protrusions, i.e., the height and the deflection angle, was also parametrically varied to study its effect on the hot spot heat flux. The results thus obtained for the flat plate case were compared to existing correlations in the open literature from a similar previous study at a much higher Reynolds number range. Since a mismatch was observed between the results of the current experiments and the existing correlations, a new empirical correlation has been developed to predict the hot spot heat flux, that is valid within the range of flow conditions studied here. A similar attempt was made for the case of the cone model, for which no previous correlations exist in the open literature. However, a global correlation covering the entire range of flow conditions used here could not be formed. A correlation that is valid for just one out of the five flow conditions used here is presented for the cones with sharp and blunt nose tips separately. Schlieren flow visualization was carried out to obtain a better understanding of the shock structures near the protuberances on both models. For most cases, where the protrusion height and deflection angle were large enough to cause flow separation immediately upstream of the protuberance, a separation shock was manifested which deflected some part of the boundary layer above the protuberance, while the rest of the fluid in the boundary layer entered a recirculating region in the separated zone before escaping to the side. Some preliminary computational analysis was conducted which confirmed this qualitatively. However, the quantitative match of surface heat flux between the simulations and experiments were not encouraging. Schlieren visualization revealed that for the flat plate case, the foot of the separation shock was located at a distance of 10.5 to 12 times the protrusion height ahead of it, whereas in the case of the sharp cone, it was at a distance of 9 to 10.5 times the protrusion height. The unsteady nature of the separation shock was also captured and addressed. Some preliminary experiments on boundary layer tripping were also conducted, the results of which have been presented here. From this analysis, it has become evident that a single global correlation cannot be formed which could be used for a wide range of flow conditions to predict the hot spot heat flux in interference interactions. The entire range of conditions that may be encountered during hypersonic flight has to be broken down into sections, and the interference heating pattern should be studied in each of these sections individually. By doing so, a series of different correlations can be formed at the varying flow conditions which will then be available for high-speed aircraft designers.

An issue of inhalation therapy is a complex topic, actively discussed in last decades, and its progress in various scientific fields is more than required. First part of this thesis brings a theoretical introduction into principles of aerosol therapy and into the requirements resulting from them. Commonly available technologies of inhalers and nebulisers for medical usage, parameters that determinate their effectivity are briefly described. Usage mistakes influencing the effectivity of inhalation are discussed, as well. Second part deals with experimental measurements of aerosol that selected inhalers generate. It also describes difficulties connected with the methods of these measurements, with sampling and following analyses. Gained results are compared with an available literature.

The present time demands emission-free and carbon-free sources of energy. This fact is not only subject of international agreements and European Union regulations, but also the state of environment points out to an essential change in energy generation of mankind. Tidal stream provides very stable and predictable source of “green” energy. Compared to other renewable energy sources tidal stream turbines in exceptional localities are able to supply energy continuously, making them base load source. The aim of the thesis was to create an extensive document with recent tidal stream power information, which has not been available in Czech language yet. Last part of the research is focused on co-locating tidal stream and off-shore wind turbines. Second part of the thesis is dedicated to aerodynamic design of single-stage horizontal axis tidal stream turbine with rated electric power of 1 MW. Calculation according to the blade cascade theory was used to design blade geometry and to find rotor diameter of 14 meters for rated stream velocity of 3.05 m/s.

This master thesis focuses on designing of an external six-component balance. This universal concept would provide access of results from different models of wings, aircraft and automobiles with relatively small scales. This work also includes theoretical background needed in aerodynamic testing, analysis of 1D beam element model of scale and explanation of components used in scale. Lastly methods of calibration and measurement in aerodynamic tunnel are described, which can be adopted for this design to achieve the adequate level of accuracy.

This master´s thesis focuses on effect of acoustic microclimate in non-production buildings to human. Within elaboration this topic was made measurment acoustic power level and created protocols by valid technical standards and law. I dedicate to damping noise and aerodynamic noise in airconditioning in part topic analysis. The part aplication on real object deal with assessment current status and draft measure for improve acoustic ratio in laboratories in center of research located in Brno. That includes describe of air-cndition unit and development two variants and their rating.

The present thesis is concerned with air flow over lightweight footbridge. Special attention is paid to flow-induced instabilities. The thesis opens with a theoretical elaboration on the phenomena related to the research matter. The next part investigates air flow over footbridge in a specific situation using numerical simulation in the Ansys CFX software. Finally, results are discussed in the light of chosen theoretical framework and relevant conclusions are presented.

The object of the diploma thesis is a preparation of fundamentals for realization for replica of the aircraft L-40 „Meta Sokol“ matching the requirements of Certification Specification for Very Light Aeroplanes (CS-VLA). The preamble of the work deals with the changes made on the original aircraft necessary to satisfy the criterias of the above-mentioned specification. One of the main contents of the first part of the thesis is the definition of replica’s basic dimensions and preparation of aerostatic fundamentals, including longitudinal stability control. As next a suitable engine is chosen and calculation of corresponding performances is made. A detailed weight analysis and a determination of centre of gravity position (c.g. position), important for solving the stability of an airplane, is also presented. Finally, a brief description of the manufacturing process of individual components and also factors influencing the technology are discussed.

This diploma thesis investigate the question of combined production of heat and power by the gasification of biomass. The introduction describes basic dilemma energy conversion from biomass. Further, special attention at the gasification technology and it´s usage at combined heat and power production is paid. The main section includes schematic proposal cycle with use of microturbine 80 [kWe] as well as basic calculation, which serves as a base for folowing project optimization. For discussed optimization is made concept of configuration, thermal and aerodynamics calculation for both heat exchangers B1 and B2. Last but not least these heat exangers were compared by different aspects such as influence of deposits on power transfer and pressure loss. At the end of the work calculated numeric values are discussed and the project of heat exchanger with it´s advantages for practise are summarised.

This master’s thesis deals with design of technological system for heating and process steam generation. The source of energy is a cogeneration unit. The thesis is divided into several parts. The first part is design of technological system and description. The second part is realized stoichiometric calculation and the thermal balance of steam boiler. The main part of thesis is design of the waste heat steam boiler. The thermal calculation, aerodynamic calculation, hydraulic calculation and strength calculation were made. The thesis also includes the drawing of designed waste heat steam boiler.

De nombreux procédés actuels mettent en jeu des écoulements diphasiques (sprays agricoles, pharmaceutiques, peinture...). Néanmoins, la connaissance des mécanismes régissant les interactions entre les phases (entraînement, modification des trajectoires des particules, transfert d'énergie...) est encore incomplète, notamment lors de l'injection directe essence, qui représente le cadre de cette étude. Dans cette étude expérimentale, les dynamiques instantanées des deux phases sont étudiées dans un plan pour mettre en évidence les interactions aérodynamiques entre les phases. Pour ce faire, un diagnostic de FPIV diphasique, utilisant un colorant fluorescent pour chaque phase, est développé afin d'acquérir simultanément des images séparées de chaque phase sur deux caméras indépendantes. Ainsi, les vitesses instantanées et simultanées des deux phases sont mesurées sans recourir à un prétraitement des images. Dans un premier temps, ce diagnostic optique est appliqué à la caractérisation d'une injection dans un gaz au repos. L'injection du spray met en mouvement le gaz par le biais d'un transfert de quantité de mouvement du spray vers le gaz. La dispersion des gouttes du spray et le mélange des deux phases qui résultent de ces transferts d'énergie cinétique dépendent du type de spray et également de la pression d'injection. Dans un second temps, ces interactions sont étudiées dans un moteur monocylindre transparent. La comparaison entre les fonctionnements avec et sans injection indique un impact notable de la présence du spray sur l'aérodynamique interne par le développement de nouvelles structures et la modification des caractéristiques du tumble. L'aérodynamique interne du moteur modifie également le développement du spray en comparaison de l'injection dans un gaz au repos. / Two-phase flows are involved in numerous actual industrial processes (agriculture, pharmacy, painting...). However, the complex interactions between phases (entrainment, particle trajectory modification, energy transfer...) are not well understood, especially for the gasoline direct injection, which represents the context of this study. For this experimental study, instantaneous dynamics of both phases are studied in a plan to highlight the aerodynamic interactions between phases. To achieve that, a two-phase FPIV diagnostic, based on using a fluorescent dye for each phase, is developed to simultaneously acquire separated images of each phase on two independent cameras. Instantaneous and simultaneous velocities of both phases are measured without any image pre-processing. Firstly, this optical diagnostic is applied to the characterisation of a spray injection in a gas at rest. The spray drags the gas by a momentum transfer from spray to gas. The spray droplet dispersion and the mixture between the two phases, which result from this kinetic energy transfer, depend on the spray topology and the injection pressure. Then, these interactions are studied in a transparent monocylinder engine. The comparison between cycles with and without injection reveals a significant impact of the spray presence on the internal aerodynamic through the development of new structures and the modification of tumble characteristics. The internal aerodynamic also modifies the spray development in comparison to the injection in a gas at rest.