Mach 4 performance evaluation of hypersonic pre-cooled turbojet engine

Abstract

Hypersonic pre-cooled turbojet engine has been tested in a propulsion wind tunnel. The engine is assumed to be used for hypersonic transport aircraft and it has a capability to operate from Mach 0 to Mach 5. The engine operating condition is evaluated with precooling and afterburning using liquid hydrogen under Mach 4 simulating flight condition. As results, it was confirmed that the position of normal shock wave in the intake can be changed by changing the throat height of the variable geometry intake. Combustion of both in the afterburner and in the core engine burner was attained using the pressure stable condition, which is attained by the variable geometry air intake. External combustion at the near downstream of the exhaust nozzle was not observed.