Computational analysis of plasma actuation for control of shock-laden flows in scramjet isolators

Kilduff, Sam

Permalink

https://hdl.handle.net/2142/132573 Copy

Description

Title

Computational analysis of plasma actuation for control of shock-laden flows in scramjet isolators

Author(s)

Kilduff, Sam

Issue Date

2025-12-05

Director of Research (if dissertation) or Advisor (if thesis)

Bodony, Daniel J

Department of Study

Aerospace Engineering

Discipline

Aerospace Engineering

Degree Granting Institution

University of Illinois Urbana-Champaign

Degree Name

M.S.

Degree Level

Thesis

Keyword(s)

• computational fluid dynamics
• plasma actuators
• shock wave-boundary layer interactions
• hypersonics
• propulsion
• scramjets

Abstract

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.

Graduation Semester

2025-12

Type of Resource

Thesis

Handle URL

https://hdl.handle.net/2142/132573

Copyright and License Information

Copyright 2025 Sam Kilduff

Owning Collections