Research Article
Numerical Investigation of an Axisymmetric Model Scramjet Assisted with Cavity of Different Aft Wall Angles
Table 1
Inlet and fuel nozzle boundary conditions [
23].
| | Parameters | Inlet | Fuel nozzles |
| | Mach number, | 4.5 | 1.0 | | Total temperature, | 2196 | 300 | | Static temperature, | 444 | 264 | | Total pressure, | 164.7 | 57.1 | | Static pressure, | 0.55 | 31.4 | | Mass fraction of O2, | 23.30 | 6.99 | | Mass fraction of N2, | 76.70 | 23.01 | | Mass fraction of C2H4, | 0 | 70.00 |
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