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Abstract
The paper analyzes the results of simulation of a supersonic air flow about simple 3D forms in order to use them for applying protective coatings to the surface with varying thickness by means of cold gas-dynamic spaying. To calculate the results, an aerodynamic analysis is performed in SolidWorks Flow Simulation software environment. Air flow zones on a streamlined surface with various characteristics (pressure, temperature, geometric shape, etc.) are analyzed, and possible methods of determination the boundaries of these zones are considered. For the solution of the control problem of applying protective coatings of varying thickness, the displacement behaviour of the movable nozzle with a small cross section is considered.
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1 Moscow Aviation Institute (National Research University), Volokolamskoe shosse 4, 125993, Moscow, Russia