CFD-Based Numerical Analysis of a Scramjet Combustor with the Dual Cavity for Inlet Mach Number at 7 with Hydrogen as a Fuel

The CFD-based numerical analysis of a dual scramjet combustor for Mach number 7 with hydrogen as a fuel has been considered by ANSYS FLUENT commercial tool. We have chosen the \({\text{H}}_{2}\) as a fuel because of high diffusivity, highest lower heating value (LHV), Higher energy density flammability limits (4–75%), and high calorific value (120 MJ/kg). This scientific study explains how the hybrid scramjet combustor’s internal fluid flow behaves. Combining well-known equations with the 2D-compressible Finite-rate/eddy-dissipation and the Reynolds-Averaged Navier Stokes (RANS) equations k-ω model of turbulence is considered for the reacting flows. The following findings are achieved using numerical analysis of a twin cavity-based scramjet combustor model. It is found that the scramjet model with a dual-based cavity is the best as compared to DLR (German Aerospace center) with the model of the semi-sphere cavity and without a cavity flame holder. Shockwave and residence time are more than Mach number 7 with a single cavity model. Scramjet’s internal fluid flow behavior with a dual cavity at Mach number 7 has been visualized. In this research analysis, it has been observed that the combustion and mixing efficiency is better compared to the single cavity scramjet and without cavity model.