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Numerical analysis of bio-mimetic concept for active flow control on wing surface
Čermák, Jakub ; Navrátil, Jan (oponent) ; Popela, Robert (vedoucí práce)
In this paper optimization on airfoil equipped with upper-side elastic flap is carried out. The optimization process is done by using of URANS CFD method. In first chapters the history of development of wing with movable flaps is briefly described. The paper continues with description and motivation on choice of computational method. Geometry and mesh generation is briefly explained. Verification and validation of computational method is also presented. The actual case study is focused on airfoil LS(1)-0417mod equipped with 20%, 30% and 40% long rigid flap on various angles of attack. The aerodynamic performance of each case is discussed together with the flow-field analysis. The non-linear structural analysis using FEM software is carried out in order to evaluate elastic flap bending stiffness and deformed shape to fulfil self-adaptive requirements.
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Numerical analysis of bio-mimetic concept for active flow control on wing surface
Čermák, Jakub ; Navrátil, Jan (oponent) ; Popela, Robert (vedoucí práce)
In this paper optimization on airfoil equipped with upper-side elastic flap is carried out. The optimization process is done by using of URANS CFD method. In first chapters the history of development of wing with movable flaps is briefly described. The paper continues with description and motivation on choice of computational method. Geometry and mesh generation is briefly explained. Verification and validation of computational method is also presented. The actual case study is focused on airfoil LS(1)-0417mod equipped with 20%, 30% and 40% long rigid flap on various angles of attack. The aerodynamic performance of each case is discussed together with the flow-field analysis. The non-linear structural analysis using FEM software is carried out in order to evaluate elastic flap bending stiffness and deformed shape to fulfil self-adaptive requirements.
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PASSIVE CONTROL OF BOUNDARY LAYER TRANSITION AND SEPARATION
Popelka, Lukáš ; Matějka, M. ; Šimurda, David ; Součková, Natálie
Particle Image Velocimetry, smoke-wire, tuft filaments and oil-flow visualization techniques were used for wind-tunnel and in-flight investigation of boundary layer separation, both stall and separation bubbles, related to the low-Reynolds number transition mechanism. Airfoils of three Czech-designed sailplanes and their wing-fuselage interaction were subject to study. Experimental data were coupled with numerical modeling and synthesis gained. Effect of passive flow control devices - vortex generators - was surveyed, counter-rotating vortex generators and Zig-zag type turbulators were applied. Separation suppression was reached and consequent drag coefficient reduction of test aircrafts measured in flight. Investigation was further extended by PIV Time-Resolved technique.
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