Abstract
Using the direct simulation Monte Carlo method, the non-Rankine–Hugoniot shock zone of steady Mach reflections with different inflow Mach numbers (five to eight) in hypersonic flows was numerically investigated. The differences in the global curvatures of the Mach stems were compared. The reduced global curvature of a Mach stem was obtained with an increased inflow Mach number when the influence of the height of the Mach stem was eliminated. The size of the non-Rankine–Hugoniot shock zone was independent of the inflow Mach number because of an approximately identical shock thickness in the considered cases. Furthermore, the feature of the pressure hot spot near the three-shock intersection was investigated comprehensively. An increase in Mach number resulted in an enhanced pressure hot spot. The boundary layers developing on both sides of the slipstream were integrated to explain and predict the formation and magnitude of the pressure hot spots, and good agreement was observed between the predicted results and the numerically simulated ones.
Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
