Designing A Shock Tunnel To Enable High Enthalpy Experimental Investigation Of Hypersonic Flows

Abstract

This study presents the design and analysis of a shock tunnel facility, utilizing existing high-pressure pipes within the UWAA department. The research aims to elucidate the trade-offs between Reynolds number, enthalpy, and test time across a range of configurations. The methodology involves using the WISTL shock tube code from the University of Wisconsin, integrated with an in-house nozzle solving code to design and model a reflected shock tunnel. The setup features a driver length of 12 f t and a driven length of 56 f t with a diameter of 7 in, achieving steady-state test durations ranging from 3 to 16 ms. This configuration enables exploration of Reynolds numbers from 106 - 108 m−1 and enthalpy conditions from 0.3 - 1.6 M J/kg. A comparative analysis with a Ludweig tube configuration, using the same pipe sections, demonstrates the shock tunnel’s capability to handle high enthalpy at higher Mach numbers without issues, offering greater flexibility. The results reveal stable stagnation conditions with minimal pressure and temperature fluctuation with changes in length but high sensitivity to driver and driven pressures. A Mach Number in the range 6 - 8 with the current test section size of 0.3m is identified as striking a reasonable balance between various parameters. In conclusion, the designed shock tunnel facility demonstrates remarkable flexibility and robust performance over test conditions and showcasing its potential for advancing research in hypersonic flow.