The invention relates to the field of experimental aerodynamics and can be used to produce hypersonic gas stream with high Mach numbers in the laboratory. The utility model is aimed at allowing the testing of the test object's influence on him hypersonic gas flow with several different Mach numbers for a single experiment. Said technical result is achieved in that the aerodynamic hypersonic shock tube comprises forming a common channel connected in series between a high-pressure chamber, the cylinder bore, hypersonic nozzle, a vacuum chamber, and overlapping channel means mounted between the high pressure chamber and the cylindrical bore. In this case, the nozzle is placed in the vacuum chamber, the tube is further provided with channel overlap means arranged between the cylindrical bore and the nozzle, the inlet hypersonic nozzle area is not more than 1% of the outlet section of cylindrical channel pipe and a channel covering means are in the form of breakable membranes. 3 z.p.f. 1 Fig.
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