Basic combustion wind tunnel test facility

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Directly-connected scramjet combustor model test and ram combustor model experiment facility

This is a Directly-connected scramjet combustor model test and ram combustor model experiment facility. The facility provides two heating methods, air flow heating via heat storage and pre-combustion using hydrogen and oxygen. Gas hydrogen and ethylene are fuels that can be supplied.


Department

Research Unit IV，Research and Development Directorate
Installation location

Kakuda Space Center
Test environment

Channel cross section: 32 mm × 147.3 mm
Mach numbers: 2.0, 2.5, 3.0
Total airflow temperature: 1000 to 2000 K (there are restrictions due to total airflow pressure)
Total airflow pressure: Standard is 1 MPa (maximum of 2 MPa)
Ventilation time: 10 seconds
Ventilation frequency: 4 to 6 times/day (pre-combustion heating), 2 times/day (thermal storage heating)

Measurement

Pressure: Scanning valve mechanical pressure sensor (48ch×3 tanks)
Temperature: 10-channel thermocouple
Gas analysis: Sampling at the exit, a maximum of 10 points simultaneously
Fuel/coolant water supply

400 mm

Fuel:
[Gas hydrogen] 0.1 kg/s × 2 systems (used after switching from ethylene supply)
[Ethylene] 0.1 kg/s × 1 system (maximum duration of 10 seconds)

Coolant water: 400 liters at 3 MPa (approx. 5 liters/second)