Abstract
Development of a large detonation-driven shock tunnel for exploring hypersonic physics is reported in this paper and its calibration results are also presented. In order to produce hypervelocity test flows with long test-duration for supersonic combustion and aerodynamic force measurement, several new techniques were proposed and investigated to improve shock tunnel performance and extend its test time. These techniques include the backwardrunning detonation driver for strong incident shock generation, the tailored interface condition for the detonation driver and the E-shaped configuration of the vacuum tank for damping wave reflections. The long-test-duration hypervelocity detonation-driven shock tunnel was developed successfully with the techniques. This shock tunnel is about 265 m in total length with a 2.5m diameter nozzle. Its performance and calibration tests were carried out and some results are presented in this paper to demonstrate its capability for duplicating hypersonic flight conditions and its reliability for heat transfer and aerodynamic force measurement study.
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