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2 Research Bulletin / Warsaw University of Technology, Institute of Aeronautics and Applied Mechanics

2 2001

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Lift characteristics of a supercritical airfoil with controlled separation in a subsonic flow

Artamonova L., Chernov L., Radtsig A., Semenchikov N., Tarkov E.

Research Bulletin / Warsaw University of Technology, Institute of Aeronautics and Applied Mechanics

2001

nr 11

1-6

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.

Interaction of jet with opposing supersonic stream in the presence of a circular flat plate

Svirschevsky S., Semenchikov N., Tarkov E.

Research Bulletin / Warsaw University of Technology, Institute of Aeronautics and Applied Mechanics

2001

nr 12

85-92

Experimental results of investigations of an interaction of a single jet with an opposing supersonic flow in the presence of a circular flat plate are presented. The tests have been performed at the free stream Mach number Moo = 1.99 and the following jet parameters: the nozzle exit Mach number Mj = 4.3, relative stagnation pressure of a jet (the interaction parameter) N = 1-1389.9. The jet expansion ratio in tests varied from n < 1 to n = 34.8. The wave structures and stagnation pressure fields near jet were investigated. The reference zones and flow regimes of interaction of a jet with opposing airflow were detected. It was established, that the value of a total pressure coefficient in these zones depended on the interaction parameter N at fixed values of the Mach numbers Moo, Mj and nozzle source geometrical parameter D = DM / dj. It was shown that the drag of a circular flat plate with a jet could be increased in comparison with the drag of an isolated plate.