Abstract
The study focuses on the problem of optimization of the shock wave system which implements the maximum total pressure. Relying on the problem solution, we selected the configuration of a supersonic air intake of external compression and carried out numerical simulation of the flow in the air intake in flight conditions with the free-stream Mach number equal to 7.5 using the ideal gas model for calculations. The system of Favre-averaged Navier — Stokes equations was supplemented by one of the turbulence models: Spalart — Allmaras model, k–ε, k–ω, and γ–Reθ. The paper deals with both two-dimensional and three-dimensional configurations of the air input and studies the influence of angles of attack, wall temperature, and free-stream Mach number on the flow characteristics. Within the research, we determined the ranges of Mach numbers corresponding to the starting mode of the air intake and described the hysteresis of characteristics at the transition of the air intake to the start-up mode for various turbulence models.
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.
