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EN
The results of experimental investigations into supercritical airfoil aerodynamics are presented. The airfoil has cross-sectional bulkheads of different heights fitted to the airfoil. The bulkheads were mounted for an active control of flow separation. The tests were carried out at the free-stream speed V[infinity] = 47 m/s within the range of angles of attack alpha= 0 ... 10 degrees. The pressure distribution around the airfoil and airfoil aerodynamic normal force, lift and drag coefficients were found. The bulkheads fitted in the airfoil leading edge neighbourhood have proved to be effective means allowing for the control of flow separation and lift of supercritical airfoils.
EN
The experimental investigations of vortex separated flows around oversimplified canard-wing-tail configurations are presented. The experiments were carried out at high angles of attack up to 40 degrees and free stream velocity V[infinity]= 37 m/s. The local flow parameters were measured for numerous points in various flow cross-sections near configurations. The integral forces and moments acting on configurations were determined also. The regions of strong interactions of vortex flows canard and wing-tail combinations with and without strakes had been discovered. It was showed that lifting performance of canard-wing-tail configurations are improved at high angles of attack by the displacement of surfaces in special manner.
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