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

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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

2001

nr 12

97-104

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.

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

1999

nr 9

135-138

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.