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Supersonic Propulsion: Inlet Shock Wave/Boundary Layer Interaction In A Diffuser, Lucas Fulop, Ian Henry, Jordan Ruffner, Anthony Mcmullen
Supersonic Propulsion: Inlet Shock Wave/Boundary Layer Interaction In A Diffuser, Lucas Fulop, Ian Henry, Jordan Ruffner, Anthony Mcmullen
Williams Honors College, Honors Research Projects
Using a finite-volume approach and ANSYS/FLUENT, supersonic flow over a 2-D ramp of varying angles is modeled. The computational results from this model will be used to further explore the design of supersonic diffusers used on military aircraft. Using grid capturing features and inflation layers, shockwave and boundary layer interactions will be observed as well as wave-associated pressure changes in supersonic turbulent flow. The Spalart-Allmaras single-equation model of turbulent flow will be used in all simulations to more accurately represent the phenomena that occur in such high-speed environments. The size of upstream zones and recirculation zones will be obtained through …
Shock Wave And Boundary Layer Interaction, Blake Keuchel, Lauren Andrews, Corryn Rahe
Shock Wave And Boundary Layer Interaction, Blake Keuchel, Lauren Andrews, Corryn Rahe
Williams Honors College, Honors Research Projects
Air entering the engine of a supersonic aircraft must be slowed to subsonic speeds for the engine to perform properly and not become significantly damaged over time. Diffusers are designed to create a shockwave to slow down air to subsonic speeds before the air enters the engine. This project will focus on the numerical analysis and design of diffuser geometries for supersonic aircraft engines. The main objective is to evaluate supersonic flow over different geometries, specifically the interaction between shock waves and boundary layer, and to minimize the amount of drag created by different diffuser geometries to optimize the efficiency …