Design and Performance Analysis of Scramjet Inlet and Isolator Systems for Hypersonic Mach Regimes

The design and analysis of a scramjet inlet and isolator system for hypersonic flight are presented. Both theoretical methods and computational fluid dynamics simulations are employed to study oblique shock compression, pressure recovery and variations in the temperature at the Mach numbers 6–10 for altitudes of 0–20 km. A grid independence study is performed using the standard k–ω turbulence model for ensuring the solution accuracy. The results show significant pressure rise and Mach number reduction at the isolator exit, with the total pressure recovery reaching up to 82% at the Mach number equal to 10 for the ground conditions. The static temperature levels at the isolator exit ranges from 1210 K (20 km, the Mach number 6) to 2740 K (sea level, the Mach number 10), posing material challenges for inlet design. The findings validate the feasibility of the proposed inlet geometry and provide critical insights into thermal management and structural design of hypersonic scramjet systems.