Stuart Craig

Stuart Craig
The University of Arizona | UA · Department of Aerospace and Mechanical Engineering

Doctor of Philosophy

About

18
Publications
3,552
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148
Citations
Introduction
Stuart Craig currently works at the Department of Aerospace and Mechanical Engineering, The University of Arizona. His research focus on the experimental study of boundary-layer stability and laminar-turbulent transition, primarily in high speed flows.
Additional affiliations
August 2016 - present
The University of Arizona
Position
  • Professor (Assistant)
April 2015 - August 2016
Los Alamos National Laboratory
Position
  • PostDoc Position
August 2009 - April 2015
Texas A&M University
Position
  • Research Assistant

Publications

Publications (18)
Article
Full-text available
The crossflow instability in a hypersonic, laminar boundary layer is investigated using point measurements inside the boundary layer for the first time. Experiments are performed on a 7° right, circular cone with an adiabatic wall condition at 5.6° angle of incidence in the low-disturbance Mach 6 Quiet Tunnel at Texas A&M University. Measurements a...
Article
Full-text available
Under the auspices of NATO STO AVT-240: “Hypersonic Boundary-Layer Transition Prediction”, this paper describes the results of close collaborations among the authors toward the fundamental understanding and modeling of the instabilities associated with three-dimensional boundary layers in hypersonic flight. Specifically, the focus is directed towar...
Article
Full-text available
Mack-mode waves are measured in a hypersonic boundary layer using high-frequency focusing schlieren deflectometry. Experiments are performed using a flared cone at angle of attack in the low-disturbance Mach 6 Quiet Tunnel at Texas A&M University across a free-stream unit Reynolds number range of. The high-frequency response of the measurement syst...
Conference Paper
View Video Presentation: https://doi.org/10.2514/6.2022-1816.vid An experimental investigation of Shock Boundary Layer Interaction (SBLI) topologies around unswept fins in Mach 5 flow has been conducted with a range of Reynolds numbers, boundary layer states, and fin-base shapes. Geometries are based on the DLR STORT flight test program, featuring...
Conference Paper
View Video Presentation: https://doi.org/10.2514/6.2021-2950.vid Calibration, commissioning, and design features of a new Mach 5 Ludwieg Tube wind tunnel at the University of Arizona are discussed. Mach-number uniformity and free-stream noise levels are measured using a Pitot rake at a range of unit Reynolds numbers at multiple spanwise and streamw...
Conference Paper
View Video Presentation: https://doi.org/10.2514/6.2021-2822.vid Plasma actuators have been developed and studied for the use of controlling hypersonic boundary layer physics. The goal is to manipulate the incoming boundary layer state to control the behavior of shock boundary layer interactions (SBLIs). The surface based plasma actuators, referred...
Conference Paper
Flow Structure and Heat Transfer Characterization of a Blunt-Fin-Induced Shock-Wave/Laminar Boundary-Layer Interaction
Conference Paper
Full-text available
The Mach 4 Quiet Ludwieg Tube (QLT4) has been successfully installed as the first operational tunnel of the Boundary Layer Stability and Transition (BLST) experimental facility at the University of Arizona. Results from an initial flow-quality and performance assessment campaign are reported. QLT4 produces Mach 4 flow that is stable across a range...
Article
Full-text available
Boundary-layer measurements were performed in a Mach 6, low-disturbance wind tunnel on a 7° cone at 5.6° angle of incidence such that the model was primarily subject to crossflow instability. Constant-temperature hot-wire anemometry was used to measure the streamwise mass flux at a series of planes normal to the cone axis. A dominant stationary wav...
Article
Full-text available
The spatiotemporal structure of a millimetric annular dielectric barrier discharge plasma actuator is investigated using a photomultiplier tube, a high-sensitivity camera, particle image velocimetry, and electrohydrodynamics simulations. Plasma actuators have typically demonstrated their utility in flow separation control, but on a millimetric scal...
Article
For many years there has been an evolving interest in controlling boundary layer transition on swept-wings. With an appropriate distribution of spanwise-periodic discrete roughness elements (DRE), subcritical wavelengths can be excited which supersede the growth of the most-amplified wavelength, thereby delaying the crossflow-dominated laminar-turb...
Conference Paper
Full-text available
The flowfield structure about annular dielectric barrier discharge plasma actuators is studied under quiescent flow conditions using particle image velocimetry. These actuators are currently under investigation for use as spanwise-periodic discrete roughness elements for laminar flow control on swept wings in both the wind-tunnel and flight. Apertu...
Article
The flowfield structure about annular dielectric barrier discharge plasma actuators is studied under quiescent flow conditions using particle image velocimetry. These actuators are currently under investigation for use as spanwise-periodic discrete roughness elements for laminar flow control on swept wings in both the wind-tunnel and flight. Apertu...

Projects

Projects (4)
Project
Calibration and commissioning of a new Mach 5 Ludwieg tube wind tunnel at the University of Arizona. Mach-number uniformity and free-stream noise level are measured using a Pitot rake at a range of unit Reynolds number conditions. Diaphragm characterization and manufacturing is also completed.
Project
Install two new wind tunnels at UA.
Project
Investigate the breakdown behavior of secondary crossflow instability in a hypersonic boundary layer.