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LES simulations of airflow around rectangle with side ratio 2:1 and their comparison with experiments
Ledvinková, Blanka ; Hračov, Stanislav ; Macháček, Michael
Our contribution is focused on the comparison of the experimental investigations and of the numerical 3D LES simulations of the airflow around sharply edged rectangle with side ratio 2:1. The rectangle object was exposed to the airflow having a given velocity at different angles of the wind attack in the wind tunnel with the aim to obtain the curves of the aerodynamic coefficients and Strouhal number depending on the impact angle. The comparative numerical 3D simulations of the wind tunnel testing were performed using COMSOL Multiphysics and OpenFoam both incorporating the Large Eddy Simulation (LES) method.
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Conceptual design of small aircraft with emphasis on structure simplicity
Rajnštajn, David ; Horák, Marek (referee) ; Jebáček, Ivo (advisor)
This thesis relates to a conceptual design of a light aircraft considering its easy manufacturability in non-professional workshop, for example at home. It is divided into three main parts. At the beginning there is mentioned a summary of existing light airplanes which determines the conceptual frame of the designed aircraft. The next part describes more detailed draft of different functional units, taking into consideration the constructional and manufacturing issues. The final part then contains basic equations to verify and define the most important characteristics of the designed aircraft.
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Conceptual design of small aircraft with emphasis on structure simplicity
Rajnštajn, David ; Horák, Marek (referee) ; Jebáček, Ivo (advisor)
This thesis relates to a conceptual design of a light aircraft considering its easy manufacturability in non-professional workshop, for example at home. It is divided into three main parts. At the beginning there is mentioned a summary of existing light airplanes which determines the conceptual frame of the designed aircraft. The next part describes more detailed draft of different functional units, taking into consideration the constructional and manufacturing issues. The final part then contains basic equations to verify and define the most important characteristics of the designed aircraft.
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