Study of the influence of the number of ramps on the efficiency, non-installed thrust and drag of a supersonic combustion demonstrator (scramjet technology)
air-breathing hypersonic propulsion; supersonic combustion; scramjet; theoretical-analytical analysis; theoretical-numerical simulation; efficiency; uninstalled thrust; drag; optimization.
This study analyzes the influence of the number of ramps on the efficiency, non-installed thrust, and drag of a supersonic combustion demonstrator (scramjet) using an engineering approach supported by analytical and two-dimensional numerical simulations in ANSYS Fluent. Five geometrical configurations, ranging from one to five compression ramps, were evaluated under flight conditions at the speed of 2050 at an altitude of 30 km. The research is based on compressible flow theories applied to the Brayton thermodynamic cycle, addressing oblique and reflected shock waves, as well as heat addition and expansion processes described by Rayleigh and Prandtl-Meyer theories. The results indicate that increasing the number of ramps enhances total pressure recovery and reduces aerodynamic drag losses, but at the expense of greater manufacturing complexity and cost. The CFD analyses showed good agreement with analytical solutions, confirming the adequacy of the proposed methodology to represent hypersonic flow behavior. Therefore, the configuration with three compression ramps was found to offer the best balance between efficiency, non-installed thrust, and structural feasibility, making it the most suitable for supersonic combustion demonstrator applications.