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- W2117297629 abstract "For the successful aerodynamic designing of a new modern aircraft it is necessary to know the accurate aerodynamic characteristics of the whole aircraft, as well as of its individual constituent parts. Since there is no adequate mathematical model of turbulent flows, we cannot solve completely the problem of aerodynamic designing by computer simulation and calculation. We still have to solve many problems related to aerodynamic designing by making tests in wind tunnels. However, wind tunnel simulation is connected with many problems which cause many distortions of flow conditions around the tested models, which finally results in inaccuracy of the measured aerodynamic values. There are many reasons for that, but it is quite understandable that even the best wind tunnels cannot provide conditions for the simulation of the flows around the tested model which would be identical to the flows in the free air. Therefore, the resolving of the problem related to the definition and elimination of the wind tunnel wall interference is a lasting task to be solved through experimental and theoretical research, either during the construction of new wind tunnels or during their exploitation. A special group of problems are related to the simulation of flows around the tested airfoil, i.e. to the provision of two-dimensional flow conditions. Paper presents the algorithm for calculating the suction of air from the working section of the wind tunnel necessary to sustain acceptable boundary layer thickness of the wind tunnel side walls, as regards successful two-dimensional wind tunnel simulation" @default.
- W2117297629 created "2016-06-24" @default.
- W2117297629 creator A5065441741 @default.
- W2117297629 date "2006-01-01" @default.
- W2117297629 modified "2023-09-25" @default.
- W2117297629 title "On Boundary Layer Control in Two-Dimensional Transonic Wind Tunnel Testing" @default.
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- W2117297629 doi "https://doi.org/10.1007/978-1-4020-4150-1_46" @default.
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