A.D. Kosinov , N.V. Semionov , A.A. Yatskikh , Yu.G. Yermolaev , G.L. Kolosov , V.L. Kocharin , A.V. Panina , V.Ya. Neyland  , A.V. Vaganov , A.Yu. Noev, A.S. Skuratov , S.V. Aleksandrov , V.I. Shalaev

DOI Number XXX-YYY-ZZZ

Conference Number HiSST 2018_12301201

The paper presents the results of experimental studies on laminar-turbulent transition at supersonic speeds performed within the framework of ITAM-TsAGI cooperation during the last decade. Experiments were carried out in the T-325 supersonic wind tunnel of ITAM SB RAS at Mach numbers 2, 2.5 and 4. For measuring the pulsations and the characteristics of the mean flow, a constant temperature hot-wire anemometer was used. The measurements were carried out on models of triangular wings with different swept angles and radii of blunting. The dimensions and characteristics of the inhomogeneities of the flow along the span of a triangular flat wing and the region of the laminar-turbulent transition in the center of symmetry of the model are determined. The most significant flow defects were fixed in the vicinity of the axis of symmetry of the triangular wing and at some distance from the center, which decreased with increasing angle of attack. Excitation of highintensity perturbations by an external Mach wave in the boundary layer of the delta-wing model with blunt lateral edges was found at Mach numbers 2, 2.5, 4. As a result of the measurements, the impact areas and mass flow pulsations in subsonic, supersonic leading edges were tested. It is shown that the maximum value of pulsations is 12-15% and varies only slightly from the conditions of the flow pattern of the delta wing.

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In Categories: High-Speed Aerodynamics and Aerothermodynamics, HiSST 2018, Hypersonic Aerodynamics, Transition to Turbulence, Turbulence Modeling and Simulation
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