Arkadii Sergeyevich Skuratov

Bio: Arkadii Sergeyevich Skuratov is an academic researcher. The author has contributed to research in topics: Boundary layer & Shock wave. The author has an hindex of 2, co-authored 4 publications receiving 7 citations.

Effects of Nose Bluntness on Hypersonic Boundary-Layer Receptivity and Stability

Abstract: High-speed laminar-to-turbulent transition over blunt bodies is relevant to a variety of aerodynamic applications. Experiments have observed that beyond a critical value of the nose radius the init...

Entropy Effect in Laminar-Turbulent Transition of the Supersonic Boundary Layer in the Wake of an Isolated Roughness

Abstract: The effect of the entropy layer generated by a small bluntness of the leading edge of a flat plate on laminar-turbulent transition of the supersonic boundary layer in the wake of an isolated roughness element (straight cylinder, 1 mm in diameter and 1 mm in height) situated on the plate surface is experimentally investigated. The bluntness radius varies. The experiments are performed at the Mach number 6 in the Reynolds number range (0.46–2.33) × 106, where the Reynolds number is based on the roughness location and the oncoming flow parameters. The reversal behavior of the roughness-induced turbulent wedges with increase in the bluntness is first revealed.

Laminar–Turbulent Transition Reversal on a Blunted Plate with Various Leading-Edge Shapes

Abstract: The influence of the flat-plate leading-edge shape on laminar–turbulent transition is investigated. Experiments were carried out at a Mach number of M∞=5; a unit Reynolds number Re1∞ from 1.5×107 t...

Influence of entropy layer on the flow over a wedge and a pair of wedges on the plate

Abstract: Influence of entropy layer generated by blunt plate leading edge on the flow over a single wedge or pair of wedges mounted on the plate is studied experimentally and numerically. Experiments are carried out in the Ludwieg type wind tunnel at Mach numbers М∞ = 5, 6 and 8 and Reynolds numbers from 7x10 6 to 27x10 6. Panoramic optical methods are used for measurements of heat flux and pressure. Flow visualization is fulfilled, as well. It is shown that even a small bluntness of the plate leading edge considerably changes the heat transfer, pressure and shear stress distributions at shock wave/boundary layer interaction, and under certain conditions it results in the change of flow structure.

Установка физического моделирования ветровой нагрузки на крановые конструкции

Abstract: The purpose of the paper is to reproduce a standard wind flow (laminar, turbulent, pulsating modes) to study the impact on crane structures, with the aim to obtain the load values of crane elements most closely approximate to real conditions. When creating an installation, which is related to the field of experimental aerodynamics, the "principle of simulating the main factors determined by the operating conditions of the research object" is adopted to ensure the r eproducibility of test results to the maximum extent. To confirm the performance efficiency of the proposed installation device, its computer model is developed using the CAD software SolidWorks. The computer model parameters are in full geometric agreement with the dimensions of the developed real installation. The use of the installation makes it possible to study the dynamic effect of the wind on the stability of crane structures in various operation modes (change in wind speed, in the mode of load operation, in operation conditions at the wall, etc.). The proposed installation allows to simulate the loads on crane equipment with the possibility of characteristics expanding, for example, its carrying capacity. The generated computer model of the installation makes it possible to reveal the physical picture of wind flow distribution at the installation outlet. The results of wind flow simulation on the proposed installation are confirmed on a computer model with a high degree of convergence of results at wind speeds of 2.5 m/s and lower The installation proposed by the authors will allow to simulate: the value of the real average statistical wind load of various intensity; pulsating component of the wind load; vortex excitation; increase of the available aerodynamic research capability for a real crane structure. The developed installation is a calibration device for external impacts of the wind force on the crane structure.