2026-09-21T12:55:29Z https://www.ideals.illinois.edu/oai-pmh

oai:www.ideals.illinois.edu:2142/132573 2026-02-20 col_2142_5131 col_2142_14800 com_2142_5130 com_2142_14799 com_2142_234

application/pdf en text Submission original under an indefinite embargo labeled 'Open Access'. The submission was exported from vireo on 2026-02-19 without embargo terms The student, Sam Kilduff, accepted the attached license on 2025-12-04 at 11:50. The student, Sam Kilduff, submitted this Thesis for approval on 2025-12-04 at 12:04. This Thesis was approved for publication on 2025-12-05 at 09:08. DSpace SAF Submission Ingestion Package generated from Vireo submission #23058 on 2026-02-19 at 18:29:12 Computational analysis of plasma actuation for control of shock-laden flows in scramjet isolators Kilduff, Sam 2025-12-05 Bodony, Daniel J computational fluid dynamics plasma actuators shock wave-boundary layer interactions hypersonics propulsion scramjets eng Scramjets offer transformative capabilities for hypersonic propulsion, but are limited by instabilities associated with shock wave-boundary layer interactions (SWBLIs). These interactions can diminish engine performance and cause unstart, an aerodynamic phenomenon that can have catastrophic consequences. Plasma actuation has emerged as a promising approach to mitigate these adverse effects due to its rapid response time and minimal mechanical complexity. This work investigates Quasi-DC (Q-DC) plasma actuators for active flow control in scramjet isolators. A computational framework was developed to model internal supersonic flows with plasma actuation. The Reynolds-averaged Navier-Stokes (RANS) equations coupled with Menter’s Shear Stress Transport (SST) turbulence model were used to simulate the flow physics, and the plasma actuators were modeled as a volumetric internal energy source term to represent the Joule heating effect of Q-DC discharges. The volume of energy deposition was formed by modeling a radial distribution around plasma filaments; this distribution was defined as a function of the turbulent kinetic energy (TKE) to incorporate the effects of flow physics on the actuation region. Simulation results demonstrated that Q-DC plasma actuation modified the structure of the shock train, shifted shock impingement locations upstream, and altered the formation of separation regions. Plasma actuation reduced overall flow distortion at the isolator exit, yielding a more favorable total pressure profile. These findings indicate that plasma-based flow control can improve isolator performance and enhance scramjet operational stability. 2025-12 Thesis https://hdl.handle.net/2142/132573 Copyright 2025 Sam Kilduff Aerospace Engineering Aerospace Engineering University of Illinois Urbana-Champaign M.S. Thesis