Supersonic Combustion
Flame stabilization in supersonic flows is an interesting topic of combustion fundamentals and also a key technology of the scramjet. To understand the fundamental mechanisms and to develop the advanced technologies of flame holding, in addition to the basic approaches like the numerical analysis of ignition and combustion in a supersonic shear layer and stagnation point flow, experimental and numerical studies on a newly devised strut, on the effect of shock waves introduced into combustion region and on a strut with preburner are being conducted.
Schematics of a space plane and a scramjet engine.
A shadow graph of shock waves and combustion region behind a triangular strut in supersonic air-flows (Ma=2.5). An interaction between incident shock waves and hydrogen combustion region has been investigated experimentally and numerically. Flame-holding characteristics can be improved by using incident shock waves.
Experimental facility.