HyShot scramjet testing in the HEG

Abstract

In this study, CFD and shock tunnel experiments have been performed, these then being compared with the flight test data from the HyShot II flight. Two new conditions for the HEG were designed analytically and refined using the one-dimensional Lagrangian code L1D and experimentally-determined efficiency coefficients, allowing the definition of a new condition with a maximum of two tests in the HEG. A new Mach 7.8 contoured nozzle was calibrated and a new piston with a braking system to prevent reverse movement after diaphragm burst was designed and tested. A wind tunnel model was developed for the HEG from the HyShot flight test model, which recreated the internal geometry at a scale of 1:1. The model was split into two engines, which were instrumented with pressure transducers and thermocouples. A fuel injection system injected cold gaseous hydrogen into the flow through portholes in the wall of one combustion chamber. The model was tested at various angles of attack and equivalence ratios and testing with a nitrogen freestream was used to quantify the effect of fuel injection without combustion.