In the test model of high-lift devices swept wing with modern supercritical profile the parametric studies were performed on the VG effects on the flow in the intensive separation zone on flaps. To obtain such information is the subject of this paper. The experimental data are required to validate the computational methods, including information not only about the total impact, but also about the flow structure in the separation area. However, due to the phenomenon complexity the accuracy of these calculations is low. Currently, the possibilities of calculation methods allow estimating the VG effect on the flow in the separation area. Until recently, investigations and selection of position of conventional VG were made only experimentally. In the presence of intense flow separation the effect of conventional VG may be reduced or not occur at all. Obviously, the VG effect will depend essentially on the intensity ratio of the second harmonic vortexes and nature of flow separation in the separation area. This is primarily the relative position of the second harmonic and the separation region on the wing and their size and position relative to each other, the orientation of the second harmonic relative to the local flow direction of the external flow, etc. The VG effectiveness depends on many parameters. Thus separated flow can be controlled when using the VG destroy large separation vortices. For example, by increasing the angle of attack of the wing separation it is highly three-dimensional picture of the flow and sufficiently sensitive to external influences. The principle of the passive VG effects on flow is to transfer the kinetic energy of the external flow separation region by the vortices system arising from the flow VG themselves. In particular, the VG are installed on the wings and nacelles of many foreign airplanes, including the most recent ones (for example, Boeing 787, Airbus A-350). 312, 67 (1996).Passive vortex generators (VG) are known as one of the ways to improve the flow of the wings and other surfaces in the presence of flow separation. Follin, “The Structure and Development of a Wing-Tip Vortex,” J. Devenport, “Two-Point Measurements in Trailing Vortices,” AIAA Paper, No. Devenport, “Seven-Hole Pressure Probe Calibration Method Utilizing Look-Up Error Tables,” AIAA J. Durston, “Seven-Hole Cone Probes for High Angle Flow Measurement: Theory and Calibration,” AIAA J. Kolb, “Plume and Wake Dynamics, Mixing, and Chemistry behind an HSCT Aircraft,” AIAA Paper, No. Starodubtsev, “Controlling flows by mini-flaps,” in: Abstracts of International Conference “Fundamental problems of High-Speed Flows”, Central Aerohydrodynamics Institute, Moscow (2004), 259. Yang, “Computational Analysis of Wake Vortices Generated by a Notched Wing,” AIAA Paper, No. Faghani, “Near-Field Wing Tip Vortex Measurements via PIV,” AIAA Paper, No. Nickels, “Trailing Vortices from a Wing with a Notched Lift Distribution,” AIAA J. Spalart, “Active-Control System for Breakup of Airplane Trailing Vortices,” AIAA J. Graham, “Optimising Wing Lift Distribution to Minimize Wake Vortex Hazard,” Aeronaut. Rossow, “Lift-Generated Vortex Wakes of Subsonic Transport Aircraft,” Progr. Lawton, “Experimental Study of the Structure of the Wingtip Vortex,” AIAA Paper, No. Bradshaw, “Mean and Turbulence Measurements in the Near Field of a Wingtip Vortex,” AIAA J. Zheng, “Measurements in Rollup Region of the Tip Vortex from a Rectangular Wing,” AIAA J. Katz, “Near-Field Behavior of a Tip Vortex,” AIAA J.
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