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Abstract
Hypersonic aerodynamic shock tube is used for comparison (validation) of the developed computer codes for the calculation of aerothermodynamics. Experiments in vacuum chamber of hypersonic aerodynamic shock tube showed the significant boundary layer in the nozzle. An increase in the boundary layer was observed with an increase in the length of the inner surface of the nozzle. Easy method to decrease the boundary layer of the nozzle was suggested. Areas of pressure field near hypersonic nozzle with a reduced pressure in the moment of quasi-stationary flow from the nozzle were determined experimentally.
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