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<p>In this study, the Mach 6 nozzle-exit flow characteristics under different reservoir-temperature conditions were investigated using numerical and experimental methods. The axial and radial pressure distributions at the nozzle exit were measured using a pitot rake consisting of 15 probes, and the corresponding Mach number distributions were obtained through the Rayleigh pitot tube relation. The pressures at the reservoir and downstream of the piston were simultaneously measured to evaluate the steady-flow duration. The experimentally measured Mach number distributions validated the numerical predictions for all temperature conditions, confirming the axisymmetry of the nozzle-exit flow. The steady-flow duration decreased with increasing reservoir temperature and was approximately 91 ms at 373 K, 79 ms at 473 K, and 69 ms at 573 K. Furthermore, the experimental results were consistent with the suppression of nozzle-exit condensation under high-Mach-number conditions and enabled stable simulation of unit Reynolds numbers corresponding to flight altitudes of 10–30&#xa0;km. These results provide reference data for the Mach 6 flow environment of the Konkuk University Ludwieg Tube and support future applications, including free-flight experiments, aerodynamic testing, sensor calibration, and hypersonic propulsion research.</p>

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Experimental and Numerical Investigation of Mach 6 Flow in a Ludwieg Tube Under Different Reservoir Temperatures

  • 期刊论文

  • 发表日期：

    2026年7月18日

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  • Eunju Kim,
  • Minhyun Han,
  • Jongho Yi,
  • Soo Hyung Park,
  • Sang Hun Kang

摘要

In this study, the Mach 6 nozzle-exit flow characteristics under different reservoir-temperature conditions were investigated using numerical and experimental methods. The axial and radial pressure distributions at the nozzle exit were measured using a pitot rake consisting of 15 probes, and the corresponding Mach number distributions were obtained through the Rayleigh pitot tube relation. The pressures at the reservoir and downstream of the piston were simultaneously measured to evaluate the steady-flow duration. The experimentally measured Mach number distributions validated the numerical predictions for all temperature conditions, confirming the axisymmetry of the nozzle-exit flow. The steady-flow duration decreased with increasing reservoir temperature and was approximately 91 ms at 373 K, 79 ms at 473 K, and 69 ms at 573 K. Furthermore, the experimental results were consistent with the suppression of nozzle-exit condensation under high-Mach-number conditions and enabled stable simulation of unit Reynolds numbers corresponding to flight altitudes of 10–30 km. These results provide reference data for the Mach 6 flow environment of the Konkuk University Ludwieg Tube and support future applications, including free-flight experiments, aerodynamic testing, sensor calibration, and hypersonic propulsion research.