A Preliminary Research on Combustion Characteristics of a Novel-Type Scramjet Combustor

Table 3

Boundary conditions.

	Air inlet	H2 inlet
Inlet Mach number	2.0	1.0
Velocity (m/s)	730	1200
Temperature (K)	340	250
Pressure (Pa)	100000	100000
Mass fraction of N2	0.736	0
Mass fraction of O2	0.232	0
Mass fraction of H2O	0.032	0
Mass fraction of H2	0	1