The successful development of the long-test-duration hypervelocity detonation-driven shock tunnel was demonstrated with performance tests. The shock tunnel performance were achieved due to these techniques discussed in the paper, such as the detonation driver with the acetylene/oxygen mixture, the tailored-interface operation condition for detonation drivers, the shock/boundary interaction control at the end of the driven section, and the E-shaped configuration of the vacuum tank. The shock tunnel is capable of duplicating the flight conditions for Mach 5～9 at altitude of 25km～50km. Large scale test flows with more than 100ms test duration can be generated at reasonable operation expanse. Hypersonic boundary layer development, scaled-model effects, hypersonic propulsion, integrated vehicle/engine are possible to test. The facility will be a useful tool for investigating into fundamental physics in hypersonic and high-temperature gas flows.
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