Abstract
Models of the ExoMars spacecraft [1-3] and variants of the X-43 air intake [4-9] were first tested in the hypersonic aerodynamic shock tube (HAST) [10-13] facility. The shock-wave structures of the gas flow under Mach numbers M=7...4.5 around the model surfaces were filmed by high-speed video camera. The obtained data were analyzed using image recognition software systems. Preliminary estimates of the flow behavior over the investigated models in the test section of the installation during the whole test are given.
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