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Preparation for test experiments in a hypersonic aerodynamic shock tubeстатья
- Авторы: Ruleva L.B., Solodovnikov S.I.
- Сборник: Conf. Proc. 2549, 070005 (2023) https://doi.org/10.1063/5.0107901
- Серия: doi.org/10.1063/5.0107901
- Том: 2549
- Год издания: 2023
- Место издания: AIP Conf. Proc. 2549
- Первая страница: 1
- Последняя страница: 5
- Номер статьи: 070005
- Аннотация: The laboratory installation HAST is preparing for test experiments. The characteristic modes for experimental tests are based on the results of numerical simulation of gas flow parameters in the working and measuring parts in a hypersonic shock wind tunnel are identified. The parameters in the low-pressure channel and at the nozzle inlet are experimentally was investigated. An increase in the pressure in the incident and reflected shock waves at the nozzle inlet was shown with an increase in the pressure in the low-pressure chamber. At the maximum values of the stagnation pressure in the plug at the entrance to the nozzle, the glow of ionized gas was observed. Experimental graphs of the pressure at the nozzle inlet and the ionization signals were presented. The temperature of the region behind the nozzle section and at a distance from it when the aerodynamic unit was evacuated to different vacuum depths is measured. Certified sensors and laboratory-made sensors located on the plate were used. The acceptability of using laboratory calorimetric sensors was shown. Fragments of visualization of shock-wave structures behind the nozzle section were presented.
- Добавил в систему: Рулева Лариса Борисовна