Shock waves analysis of the novel intake design system for a scramjet propulsion

Abstract

The supersonic combustion scramjet in the inlet applies the shock waves compression mechanism to substitute the actual compressor from a gas turbine engine. The scramjet works with combustion of fuel through the air stream in supersonic condition at least with Mach 5. Novel design of a scramjet intake system was made with variations in the angle of the fins and entrance width. The best combination of diameter and inclination angle was 1.75 m and 15 degrees, respectively. The findings were able to increase the oblique shock wave interactions and supplicate effective combustion and reduce pressure losses for the effective application of scramjet system. © 2021 World Scientific and Engineering Academy and Society.

keywords: CFD; Compression; Density change; Intake; Mach number; Pressure loss; Scramjet; Shockwaves