Wyniki wyszukiwania - BazTech

1

Supersonic low interaction with absorbing surface

Svirschevsky S., Nikitchenko Y.

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

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2001

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nr 12

93-96

EN

This paper is devoted to investigation of shock wave rise conditions ahead of an absorbing surface. The study was based on the numerical solution of the model of kinetic equations BGK in an integral form. It was found that the boundary between the regions of steady, non-steady modes in one-dimensional problem corresponds to the boundary of the shock wave existence area for a multi-dimensional problem.

2

Study a multi-body aerodynamic interference in supersonic flow

Svirschevsky S., Semenchikov N., Korolev N., Tarkhow E.

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

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2001

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nr 12

97-104

EN

The experimental results of investigations into aerodynamics of two bodies for their different orientations relative to each other in a supersonic flow are presented. The first body was the spherical segment fitted to blunt conical boattail. The second was the hollow convergent cone with a spherical afterbody. The tests were carried out in the sub-trans-supersonic closed layout wind tunnel T-2 MAI at the free stream Mach numbers M[infinity] = 1.3-2.5 and at angles of attack ranging from 0° to 180°. The investigations were conducted for several distances between bodies. The coefficients of a normal force, an axial force and a pitching moment of these bodies were found. The flow visualizations were made to obtain the flow structures around the experimental models. The new data on aerodynamics of dividing objects enabling one to define their longitudinal static stability are obtained with a high degree of accuracy. The results of these investigations have showed the big influence of aerodynamic interference on the performances of the discussed configurations.

3

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

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2001

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nr 12

85-92

EN

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.

4

Aerodynamics of a half-wing in supersonic flow

Svirschevsky S., Semenchikov N., Tarkhow E., Chernov G.

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

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1999

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nr 9

135-138

EN

Experimental results of the aerodynamic normal forces and moments of the semispan wing models are presented. All tests have been conducted at free stream Mach numbers M[infinity] = 1,5... 2,5, the angles of attack alpha= -4o ... 26° and the angles of sideslip beta= 0°...20°. Mounting effects on the model aerodynamic properties are considered. The test results of the semispan models can be used for a prediction of aerodynamic properties of sideslipping half-wings in a supersonic flow.