Departamento de Ciências Aeroespaciais
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Browsing Departamento de Ciências Aeroespaciais by Field of Science and Technology (FOS) "Ciências Naturais::Ciências Físicas"
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- Development of an open source software tool for propeller design in the MAAT projectPublication . Morgado, João Paulo Salgueiro; Silvestre, Miguel Ângelo Rodrigues; Marques, José Carlos PáscoaThis thesis presents the development of a new propeller design and analysis software capable of adequately predicting the low Reynolds number performance. JBLADE software was developed from QBLADE and XFLR5 and it uses an improved version of Blade Element Momentum (BEM) theory that embeds a new model for the three-dimensional flow equilibrium. The software allows the introduction of the blade geometry as an arbitrary number of sections characterized by their radial position, chord, twist, length, airfoil and associated complete 360º angle of attack range airfoil polar. The code provides a 3D graphical view of the blade, helping the user to detect inconsistencies. JBLADE also allows a direct visualization of simulation results through a graphical user interface making the software accessible and easy to understand. In addition, the coupling between different JBLADE modules avoids time consuming operations of importing/exporting data, decreasing possible mistakes created by the user. The software is developed as an open-source tool for the simulation of propellers and it has the capability of estimating the performance of a given propeller geometry in design and off-design operating conditions. The current development work was focused in the design of airship propellers. The software was validated against different propeller types proving that it can be used to design and optimize propellers for distinct applications. The derivation and validation of the new 3D flow equilibrium formulation are presented. This 3D flow equilibrium model accounts for the possible radial movement of the flow across the propeller disk, improving the performance prediction of the software. The development of a new method for the prediction of the airfoil drag coefficient at a 90 degrees angle of attack for a better post-stall modelling is also presented. Different post-stall methods available in the literature, originally developed for wind turbine industry, were extended for propeller analysis and implemented in JBLADE. The preliminary analysis of the results shows that the propeller performance prediction can be improved using these implemented post-stall methods. An inverse design methodology, based on minimum induced losses was implemented in JBLADE software in order to obtain optimized geometries for a given operating point. In addition a structural sub-module was also integrated in the software allowing the estimation of blade weight as well as tip displacement and twist angle changes due to the thrust generation and airfoil pitching moments. To validate the performance estimation of JBLADE software, the propellers from NACA Technical Report 530 and NACA Technical Report 594 were simulated and the results were checked against the experimental data and against those of other available codes. The inverse design and structural sub-module were also validated against other numerical results. To verify the reliability of XFOIL, the XFOIL Code, the Shear Stress Transport k-ω turbulence model and a refurbished version of k-kl-ω transition model were used to estimate the airfoil aerodynamic performance. It has been shown that the XFOIL code gives the closest prediction when compared with experimental data, providing that it is suitable to be used in JBLADE Software as airfoil’s performance estimation tool. Two different propellers to use on the MAAT high altitude cruiser airship were designed and analysed. In addition, the design procedure and the optimization steps of the new propellers to use at such high altitudes are also presented. The propellers designed with JBLADE are then analysed and the results are compared with conventional CFD results since there is no experimental data for these particular geometries. Two different approaches were used to obtain the final geometries of the propellers, since, instead of using the traditional lift coefficient prescription along the blade, the airfoil’s best L3/2/D and best L/D were used to produce different geometries. It was shown that this new first design approach allows the minimization of the chord along the blade, while the thrust and propulsive efficiency are maximized. A new test rig was developed and used to adequately develop and validate numerical design tools for the low Reynolds numbers propellers. The development of an experimental setup for wind tunnel propeller testing is described and the measurements with the new test rig were validated against reference data. Additionally, performance data for propellers that are not characterized in the existing literature were obtained. An APC 10”x7” SF replica propeller was built and tested, providing complementary data for JBLADE validation. The CAD design process as well as moulds and propeller manufacture are also described. The results show good agreement between JBLADE and experimental performance measurements. Thus it was concluded that JBLADE can be used to design and calculate the performance of the MAAT project high altitude cruiser airship propellers.
- Modelling of spray-wall impingementPublication . Rodrigues, Christian Michel Gomes; Silva, André Resende Rodrigues da; Barata, Jorge Manuel MartinsWhen a drop collides with an interposed surface, three phases are usually involved: liquid (the drop), solid (the substrate) and gas (the surrounding environment). Such an event involves a number of parameters associated with the physical characteristics of the incident particles, the properties of the target surface, and the natural features of the air flow. Each occurrence leads to a singular outcome, since each particle experiences a different reality throughout the injection cycle. Therefore, the development of appropriate modelling strategies of this complex multi-phase flow requires a thorough understanding of the mechanisms underlying the spray impingement process. Several computational models have been reported in the open literature, although not always successfully. From these, only a few have attempted to replicate the more intricate scenarios that include the formation and development of a liquid film over the surface due to the deposition of previously injected particles, the presence of a high velocity cross-flowing gas, and the thermal effects promoted by the existence of hot walls. Even though these elements are some of the more influential parameters affecting the final outcome of spray-wall impacts, most of the simulations still neglect some of them in their formulation. Therefore, in order to capture the majority of the physical phenomena observed in experimental studies, CFD codes must be equipped with superior mathematical formulations. During the present doctoral research, three independent computational extensions have been devised and integrated into the model used by our research group to simulate spray-wall interactions. The upgrades — that have been proposed over the course of the study — have been denominated as the liquid film, evaporation and breakup sub-models. They are intended to complement the basic mathematical formulation adopted in the original simulation procedure. This approach has contributed to enhance the prediction capabilities of the model, since it is now capable of capturing some phenomena that were not considered previously. On the other hand, it has also extended the range of applicability of the CFD code to a new set of impact conditions (i.e., in hot environments and with a high velocity crossflow). Furthermore, the present work provides a detailed analysis of the results obtained, with major emphasis given to the disintegration mechanisms and secondary droplet characteristics. Both quantitative and qualitative comparisons between computational and experimental results are presented. When pertinent, the impact of a particular sub-model onto the outcome predicted is also evaluated by comparing the versions of the model with and without the corresponding computational extension. Moreover, a systematic approach is adopted at each section to infer the influence of different parameters on the final outcome. This methodology has been decisive to better understand the factors affecting the phenomena occurring during impact.