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Development of a Shock Tube for Improvement of Reentry Flight Technology
JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
A free piston double diaphragm shock tube with 70 × 70 mm cross-section at test section was newly developed for the purpose of investigating nonequilibrium phenomena behind a shock wave. This paper presents the performance of the shock tube and the measurement system newly developed. Experimental investigation to clarify its characteristics was conducted for various operational parameters, such a rupture pressure of the first diaphragm and initial pressures of the low pressure tube, the highdoi:10.2322/jjsass.57.426 fatcat:amrj2q6j3ja6bojhgj76ozi7ni