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Wing leading edge active flow concept analysis
Mahdal, Vít ; Zikmund, Pavel (referee) ; Popela, Robert (advisor)
This research is focused on substitution of commonly used High-Lift devices by active flow control on the wing leading edge. The analysis is done by CFD tools with use of Reynolds-Averaged Navier-Stokes (RANS) method. In the beginning of the research, commonly used High-Lift devices are described. Solver setting and its explanation together with verification and validation is described in the following chapters. An active flow control concept is testing at the LS(1)-0413 airfoil, for 5 different positions of slots, two different slots widths (h/c= 0,0025 and 0,005) and two different blowing velocities (v_Jv_=2,22 and 4,44). In the end of this paper, physical phenomena of blowing is described together with evaluation of different cases. The best case is compared with Fowler and slotted flap at Reynolds number 2,2 million.
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Aerodynamic characteristics of airfoils
Foltýn, Pavel ; Cejpek, Jakub (referee) ; Koutník, Tomáš (advisor)
This bachelor´s thesis describes an influence of geometric characteristics of an airfoil on its aerodynamic properties. The first part of the thesis defines airfoil, describes its geometric characteristics, emergence of aerodynamic forces and convection around airfoil. The second part deals with influence of profile geometry on aerodynamic properties of airfoils. It is shown on NACA four and six digit profiles, in their buoyancy and moment lines and polars. The last part deals with wind tunnels and measurement in them. The thesis focuses on forces and moments measurement by force balances and static and total pressure measurement. Velocity measurement is focused on the laser Doppler velocimetry, on the hot-wire velocity probe and PIV method. Very briefly selected flow visualization methods are shown there. Comparison of profile characteristic obtained by measuring in wind tunnels and numerical simulation in Xfoil program is also shown there.
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High performance paraglider aerodynamic optimization
Grim, Robert ; Navrátil, Jan (referee) ; Popela, Robert (advisor)
This thesis is focused on the aerodynamic analysis of the competition paraglider wing. Drags of the particular wing parts are divided into chapters. The aim was to get a grasp of sizes of the individual components drags in relation to the entire assembly. In the first instance, a 2D profile and then the entire configuration of the 3D wing was analyzed. After the evaluation, some power reserves were detected in an airfoil and so the airfoil shape was optimized. After the optimization of the individual components, the CFD calculation was used again. At the end, geometry changes were evaluated.
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Aerodynamics Parametric Shape Aircraft Optimization
Dofek, Ivan ; Salga, Jaroslav (referee) ; Brož,, Václav (referee) ; Fiľakovský, Karol (advisor)
The work deals with the use of geometric parameterization for shape description of some parts of the airplane. Geometric parametrization is used for creating a parametric model airfoil. This parametric model allows local deformations pobrchu profile and can easily be applied to generate the geometry of the wing or other parts letoumu. Some properties of the parametric model were tested applications in aerodynamic optimization. Furthermore, the work deals with the parametric description of the blades, the aerodynamic optimization and noise analysis. For propeller blade were created distribution function of the control parameters that can be used in aerodynamic optimization of the blades. Geometric parameterization is used for identifying the location and other characteristics of noise sources.
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Surrogate-assisted Evolutionary Computation
Konečný, Štěpán ; Dobrovský, Ladislav (referee) ; Kůdela, Jakub (advisor)
This thesis deals with the optimization of flight profile design using surrogate models with differential evolution. The aim was to become familiar with the problem and possible solution procedures. The main objective was to create a surrogate model, implement it on the problem and then optimize it. In the introduction of the paper, the used surrogate models and evolutionary algorithms are described in detail. Subsequently, the control method, the optimization of expensive problems, the data acquisition issues for surrogate models and examples of practical applications of surrogate models are described. The paper concludes with a description of the optimization procedure and the results obtained by optimizing the flight profile design using the selected surrogate models, followed by an evaluation.
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Comparison of panel codes for aerodynamic analysis of airfoils
Bilčík, Adam ; Schoř, Pavel (referee) ; Popela, Robert (advisor)
Cieľom tejto práce bolo vytvorenie prehľadu v súčasnosti používaných implementácií panelových metód pre aerodynamické výpočty charakteristík 2D profilov. Základný popis princípu panelovej metódy, porovnanie jednotlivých implementácií a zhodnotenie ich možností (presnosť, aplikovateľnosť) na typické úlohy. V práci boli použité tri rôzne panelové programy: Xfoil, JavaFoil a XFLR5. Práca bola obohatená o meranie v aerodynamickom tuneli.
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Airfoils Evolution and Summary
Kerndl, Jindřich ; Dofek, Ivan (referee) ; Zikmund, Pavel (advisor)
This bachelor thesis describes the evolution and overview of airfoils. The first part is about the airfoil characteristics and their significance. The second part reflects the historical evolution of airfoils for piston engine powered aircraft. The conclusion compares the airfoils of currently used light sport aircraft of Czech and foreign producers.
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Surrogate-assisted Evolutionary Computation
Konečný, Štěpán ; Dobrovský, Ladislav (referee) ; Kůdela, Jakub (advisor)
This thesis deals with the optimization of flight profile design using surrogate models with differential evolution. The aim was to become familiar with the problem and possible solution procedures. The main objective was to create a surrogate model, implement it on the problem and then optimize it. In the introduction of the paper, the used surrogate models and evolutionary algorithms are described in detail. Subsequently, the control method, the optimization of expensive problems, the data acquisition issues for surrogate models and examples of practical applications of surrogate models are described. The paper concludes with a description of the optimization procedure and the results obtained by optimizing the flight profile design using the selected surrogate models, followed by an evaluation.
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