Research Article
Numerical Investigation on the Effect of Inflow Mach Numbers on the Combustion Characteristics of a Typical Cavity-Based Supersonic Combustor
Figure 9
Contour plot of (a) temperature, (b) pressure at different incoming Mach numbers, and (c) pressure for Mach 2.52 describing the different shock waves formations and flow variables.
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(b) |
(c) |