Features of preparing a validating experiment in a hypersonic aerodynamic shock tube

The variety of studies on shock-wave interactions in a channel simulating the air intake of high-speed aircraft (HSA) shows an increasing number of computational and experimental studies in this area. For aerodynamic analysis of high-speed aircraft, their own computer codes are created to calculate aerothermodynamic characteristics. For the operational validation of new computer codes describing the aerothermodynamics of HSA fragments, a laboratory hypersonic shock wind tunnel (HAST) at Mach numbers M=5-7 is used. The regimes with a long time of the quasi-stationary state of the flow in the shock and aerodynamic parts of the HAST are revealed. There is a preliminary validation, in which the parameters of the gas flow are compared according to the calculations and experiments in the shock part of the HAST before entering and leaving the nozzle. Registration of parameters on the surface of models in the flow is carried out by direct measurements by certified pressure sensors without intermediate calculations. Regular calibration of non-certified sensors by certified sensors in separate modes is possible. Good repeatability of experiments is provided by a solenoid valve with a millisecond response. Improving the reliability of experimental data depends on the implementation of the international standard by the operator, the use of certified direct measurement sensors, resetting the nozzle boundary layer during the action of a quasistationary period, and increasing the lifetime of the quasistationary state of the flow. Expanding the range of validated parameters in HAST requires the use of high-speed visualization tools for shock-wave structures and measuring instruments.