Pressure and Heat Flux Calibration of the Long-test-duration Hypervelocity Detonation-driven Shock Tunnel

Abstract

A large detonation-driven shock tunnel, named JF12, was developed for exploring hypersonic physics in Institute of Mechanics, Chinese Academy of Sciences. The shock tunnel is capable of duplicating the flight conditions and conducting full-scale or near fullscale model tests, which can make it easy for extrapolation of experimental data to flight. However, in view of the need for high-quality aerothermodynamic measurements in hypersonic shock tunnels, a detailed evaluation of the flowfield uniformity and standard model tests are necessary. In this paper, calibration of the Mach 8 nozzle was first presented. Pitot pressure and stagnation heat transfer data acquired using a Pitot rake were discussed to analyze the nozzle flow uniformity. Besides, a precision built 7-deg sharp cone instrumented with heat gages was used. Corresponding numerical simulations were also conducted for comparison. Results showed that good uniformity was found and a core flow region of approximately 1.8 to 2 m diameter was observed. And heat transfer measurement uncertainty was within ±10%, which was quite good in hypersonic shock tunnels currently.

Development and commissioning of the T6 Stalker Tunnel

“…As RSTs typically have test times between 1 ms and 10 ms, they are particularly suitable for the investigation of relatively long time-scale phenomena where flow enthalpy is important, such as combustion. Many large-scale RST facilities operate world wide, with capability to test up to orbital conditions (Hannemann et al 2016;Stennett et al 2020;Itoh et al 1998;Mundt 2016;Wang et al 2017;Tsai et al 2009).…”