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俄罗斯空气动力研究所中心学报

ISSN 打印: 1948-2590
ISSN 在线: 1948-2604

俄罗斯空气动力研究所中心学报

DOI: 10.1615/TsAGISciJ.2017019838
pages 685-707

ANALYSIS OF SUBSONIC VORTEX FLOW OVER THE MODEL OF MANEUVERABLE AIRCRAFT USING COMPUTATIONAL FLUID DYNAMICS METHODS

Konstantin Anatolievich Osipov
Central Aerohydrodynamic Institute (TsAGI), 1 Zhukovsky Str., Zhukovsky, 140180, Moscow Region, Russia

ABSTRACT

Numerical analysis of the aerodynamic characteristics of a model of maneuverable aircraft at high angles of attack is performed. It is shown that the dynamics and stability of the vortex structures have a significant effect on the entire model aerodynamics, especially at high angles of attack. Analysis of the flow visualization shows that increasing vortex intensity, loss of stability, vortex breakdown, and displacement of the vortex breakdown point toward the leading edge of the streamlined surface are the general characteristics of the vortex structures at increasing angles of attack. Test numerical simulations are performed in order to determine the position of the vortex breakdown depending on the angle of attack for a delta wing. Analysis of the simulation results allows stating a preliminary principle of the vortex system control in order to obtain acceptable aerodynamic characteristics at high angles of attack. It is necessary to use engineering solutions aimed at delaying the vortex breakdown and increasing the distance between the vortices to reduce or eliminate their mutual interference. The simulation results are in satisfactory agreement with the experimental data obtained during the model tests in the T-102 wind tunnel at TsAGI. These results can be interpreted as input data for further investigations with the aim of controlling the vortex flow over maneuverable aircrafts.


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