Ramjet engine test facility (RJTF)

Wind tunnel for a combustion test using a supersonic and hypersonic air-breathing engine model

This wind tunnel for a combustion test uses a supersonic and hypersonic air-breathing engine model, including for ramjets, scramjets and rocket based combined-cycle engines. It is also possible to conduct engine model tests under static atmospheric conditions.

Department	Space Technology Directorate I
Installation location	Kakuda Space Center
Measurement items	Pressure: 256 channels (electronic scanning type) 　　　66 channels (fixed, including facility data) Temperature: 57 channels (including facility data) Flow rate: 5 channels (sample supply propellant) Heat flux: 16 channels Optical observations: 500 mm Schlieren
Fuel supply	Hydrogen gas Oxygen gas Ethanol
Test environment	Facility nozzle exit diameter: 51 cm x 51 cm (free jet) ◆Mach 8 flight conditions: Combination of thermal storage heating and combustion heating 　Nozzle exit Mach numbers: 6.7 　Static temperature/static pressure: 237 K/575 Pa 　Maximum test time: 30 seconds ◆Mach 6 flight conditions: Thermal storage heating or combustion heating 　Nozzle exit Mach numbers: 5.3 　Static temperature/static pressure: 222 K/2.6 kPa 　Maximum test time: 60 seconds ◆Mach 4 flight conditions: Thermal storage heating 　Nozzle exit Mach numbers: 3.4 　Static temperature/static pressure: 217 K/5.5 kPa 　Maximum test time: 60 seconds *Given the assumption for air flow after the shockwave passage from the front edge of the vehicle, the Mach number flight conditions and facility provision Mach number differ.
Year of completion	FY 1993