Abstract
Longer working time of the hypersonic aerodynamic shock tube has been demonstrated by applying modelling and experiment. This facility is a short-term installation. It is used to validate the results of aerothermodynamic characteristics of aircraft modelling calculated using national computational codes. Numerical modeling and experimental data results are compared. Quasi-stationary state of the gas flow in operating time of the installation requires sufficient time. A review of publications about increasing the working time of shock tubes for initiation of high-speed gas flows was made. Some models of shock tubes with longer working time have been selected for discussion. The computational studies for hypersonic aerodynamic shock tube showed a positive trend for one of the operating modes. A simulation for a regular and lengthened shock tube facilities was carried out, taking the flow as in viscous medium and using Euler equations. The effectiveness of lengthening the low pressure channel section of the facility was shown by modelling. The low pressure chamber was elongated by 3m to the existing hypersonic aerodynamic shock tube.
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