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 |
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Installation location | Kakuda Space Center |
Test environment | Channel cross section: 32 mm × 147.3 mm |
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: Coolant water: 400 liters at 3 MPa (approx. 5 liters/second) |