Ground Testing of the HyShot II Scramjet Configuration in HEG

TLDR

The main focus of these investigations was to obtain surface pressure and surface heat transfer data on the intake, cowl, body‑side surfaces of the combustion chamber, and the nozzle. Ground‑based testing of the HyShot II scramjet was performed in the High Enthalpy Shock Tunnel Gottingen (HEG) at DLR, using two operating conditions corresponding to 33 km and 27 km altitude, and CFD was employed to support analysis and predict free‑stream conditions. High‑speed flow visualization of the combustor flow was also performed.

Abstract

Ground based testing of the HyShot II supersonic combustion ramjet flight configuration was carried out in the High Enthalpy Shock Tunnel Gottingen, HEG, of the German Aerospace Center, DLR. The main focus of these investigations was to obtain surface pressure and surface heat transfer data on the intake and the cowl and body side surfaces of the combustion chamber and the nozzle. Further, high speed flow visualisation of the combustor flow was performed. Two HEG operating conditions which are related to 33km and 27km flight altitude were applied. Computational fluid dynamics (CFD) was applied to support the analysis of the experimental results and for the prediction of the free stream conditions in the HEG test section.