Basic combustion wind tunnel test facility

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 Space Technology Directorate I
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)