ORCID Profile
0000-0002-6590-3564
Current Organisation
University of Queensland
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Research Topics
In Research Link Australia (RLA), "Research Topics" refer to ANZSRC FOR and SEO codes. These topics are either sourced from ANZSRC FOR and SEO codes listed in researchers' related grants or generated by a large language model (LLM) based on their publications.
Top 5 Research Topics
ANZSRC Field of Research (FoR)
Aerospace Engineering | Hypersonic Propulsion and Hypersonic Aerodynamics | Satellite, Space Vehicle and Missile Design and Testing | Aerodynamics | Aerospace Engineering Not Elsewhere Classified | Satellite, Space Vehicle And Missile Design | Classical Physics | Combustion And Fuel Engineering | Aerospace Materials | Composite and Hybrid Materials | Fluid Physics |
ANZSRC Socio-Economic Objective (SEO)
Space Transport | Emerging Defence Technologies | Aerospace equipment | Space transport | Combined operations | Aerospace Equipment | Expanding Knowledge in the Physical Sciences | Expanding Knowledge in Engineering | Scientific Instruments | Air transport
Related Links
Publications
Near-resonant holographic interferometry of hypersonic flow
Publisher: Springer Science and Business Media LLC
Date: 03-2001
DOI: 10.1007/PL00004056
Velocimetry and Thermometry of Supersonic Flow Around a Cylindrical Body
Publisher: American Institute of Aeronautics and Astronautics (AIAA)
Date: 06-1998
DOI: 10.2514/2.479
OH concentration and temperature measurements by use of near-resonant holographic interferometry
Publisher: Optica Publishing Group
Date: 10-12-2004
DOI: 10.1364/AO.43.006384
Abstract: Near-resonant holographic interferometry is demonstrated to measure temperature and species concentration in a two-dimensional steady premixed air-acetylene flame. A peak temperature of (2600 +/- 100) K and a peak OH number density of (9.6 +/- 0.3) x 10(22) m(-3) are obtained, consistent with the expected values for such a flame. These values are determined by recording interferograms with a laser assumed sufficiently detuned from line center so that pressure and temperature broadening can be ignored. The results are thus obtained without making prior assumptions on the temperature or pressure of the flame beyond the existence of thermal equilibrium.
Optical Thickness Measurements of Vacuum Ultraviolet Radiation in the X2 Expansion Tube
Publisher: American Institute of Aeronautics and Astronautics (AIAA)
Date: 08-2016
DOI: 10.2514/1.J054659
Electrically-heated flat plate testing in a free-piston driven shock tunnel
Publisher: Elsevier BV
Date: 08-2020
High-Enthalpy Expansion Tube Experiments with Gas Injection
Publisher: American Institute of Aeronautics and Astronautics (AIAA)
Date: 12-2000
DOI: 10.2514/2.916
Observation of an Ablating Surface in Expansion Tunnel Flow
Publisher: American Institute of Aeronautics and Astronautics (AIAA)
Date: 07-2010
DOI: 10.2514/1.J050207
Improved test time evaluation in an expansion tube
Publisher: Springer Science and Business Media LLC
Date: 05-2018
On the population of the metastable states behind unstable shock waves in ionizing argon
Publisher: Cambridge University Press (CUP)
Date: 09-1986
DOI: 10.1017/S0022112086000903
Abstract: Experiments are described in which the populations of metastable levels in ionizing argon are measured through spatially resolved hook interferometry. The results are compared with the present model for shock-induced ionization and a recently proposed mechanism to explain observed flow instabilities. It is found that the experimental measurements support the presently accepted model, which states that electron–atom collisions play the dominant role in the excitation process, but contradicts recent proposals which predict a rapid build-up of anomalously high metastable populations through atom–atom collisions.
Flow tagging velocimetry in a superorbital expansion tube
Publisher: Springer Science and Business Media LLC
Date: 07-2000
Study of the Afterbody Radiation during Mars Entry in an Expansion Tube
Publisher: American Institute of Aeronautics and Astronautics
Date: 05-01-2017
DOI: 10.2514/6.2017-0212
Spectrally Filtered Imaging and Vacuum Ultraviolet Spectroscopy of Preheated Models in X2
Publisher: American Institute of Aeronautics and Astronautics (AIAA)
Date: 12-2017
DOI: 10.2514/1.J056021
Thermal compression effects within a fundamental, hydrogen-fuelled scramjet
Publisher: Elsevier BV
Date: 03-2021
Three-dimensional effects on line-of-sight visualization measurements of supersonic and hypersonic flow over cylinders
Publisher: Springer Science and Business Media LLC
Date: 28-02-2007
Quantitative SLM-based differential interference contrast imaging
Publisher: Optica Publishing Group
Date: 15-06-2010
DOI: 10.1364/OE.18.014063
Enhanced flow visualization with near-resonant holographic interferometry
Publisher: Optica Publishing Group
Date: 08-2003
DOI: 10.1364/AO.42.004445
Abstract: Holographic interferometry measurements have been performed on high-speed, high-temperature gas flows with a laser output tuned near a resonant sodium transition. The technique allows the detection and quantification of the sodium concentration in the flow. By controlling the laser detuning and seeded sodium concentration, we performed flow visualization in low-density flows that are not normally detectable with standard interferometry. The technique was also successfully used to estimate the temperature in the boundary layer of the flow over a flat plate.
Experimental evidence of the impact of radiation coupling on binary scaling applied to shock layer flows
Publisher: Elsevier BV
Date: 05-2018
Hypersonic shock impingement on a heated flat plate at Mach 7 flight enthalpy
Publisher: Cambridge University Press (CUP)
Date: 07-12-2020
DOI: 10.1017/JFM.2020.877
Emission and Holographic Interferometry Measurements in a Superorbital Expansion Tube
Publisher: American Institute of Aeronautics and Astronautics (AIAA)
Date: 06-1998
DOI: 10.2514/2.478
PLIF thermometry in shock tunnel flows using a Raman-shifted tunable excimer laser
Publisher: Springer Science and Business Media LLC
Date: 10-1998
Experimental study of Saturn entry radiation with higher amount of diluent in an expansion tube
Publisher: American Institute of Aeronautics and Astronautics
Date: 24-06-2018
DOI: 10.2514/6.2018-4070
Differential interference contrast imaging using a spatial light modulator
Publisher: Optica Publishing Group
Date: 28-09-2009
DOI: 10.1364/OL.34.002988
Comparison of Experimental and Numerical Studies of Ionizing Flow over a Cylinder
Publisher: American Institute of Aeronautics and Astronautics (AIAA)
Date: 11-2003
DOI: 10.2514/2.6833
Optical imaging techniques for hypersonic impulse facilities
Publisher: Cambridge University Press (CUP)
Date: 2007
DOI: 10.1017/S0001924000001718
Abstract: The application of optical imaging techniques to hypersonic facilities is discussed and ex les of experimental measurements are provided. Traditional Schlieren and shadowgraph techniques still remain as inexpensive and easy to use flow visualisation techniques. With the advent of faster cameras, these methods are becoming increasingly important for time-resolved high-speed imaging. Interferometry’s quantitative nature is regularly used to obtain density information about hypersonic flows. Recent developments have seen an extension of the types of flows that can be imaged and the measurement of other flow parameters such as ionisation level. Planar laser induced fluorescence has been used to visualise complex flows and to measure such quantities as temperature and velocity. Future directions for optical imaging are discussed.
Nonequilibrium Radiation Intensity Measurements in Simulated Titan Atmospheres
Publisher: American Institute of Aeronautics and Astronautics (AIAA)
Date: 04-2010
DOI: 10.2514/1.44482
Simultaneous two-wavelength holographic interferometry in a superorbital expansion tube facility
Publisher: Optica Publishing Group
Date: 11-1997
DOI: 10.1364/AO.36.008128
Abstract: A new variation of holographic interferometry has been utilized to perform simultaneous two-wavelength measurements, allowing quantitative analysis of the heavy particle and electron densities in a superorbital facility. An air test gas accelerated to 12 km/s was passed over a cylindrical model, simulating reentry conditions encountered by a space vehicle on a superorbital mission. Laser beams with two different wavelengths have been overlapped, passed through the test section, and simultaneously recorded on a single holographic plate. Reconstruction of the hologram generated two separate interferograms at different angles from which the quantitative measurements were made. With this technique, a peak electron concentration of (5.5 +/- 0.5) x 10(23) m(-3) was found behind a bow shock on a cylinder.
Relaxation behind shock waves in ionizing neon
Publisher: Cambridge University Press (CUP)
Date: 06-1991
DOI: 10.1017/S0022112091000277
Abstract: Experiments in ionizing neon are described in which heavy-particle and electron densities are measured and compared with the current kinetic model. The experimental results allow a determination of the atom-atom collisional excitation cross-section constant, giving a value of (8±2) × 10 −20 cm 2 /eV for the range of conditions examined. The population of two of the excited-state levels of the atom are measured and compared with theoretical predictions. The experimental populations are found to follow the expected behaviour in the quasi-equilibrium region, but are several orders of magnitude higher than predicted in the nonequilibrium zone. These findings suggest that the depopulation of excited states through ionizing collisions occurs more slowly than expected. Absorption linewidths and line shifts are also measured in the quasi-equilibrium region and found to compare well with theory. A small precurson population is also observed and population measurements in this region are compared with other experimental results in argon and krypton.
Hypersonic shock impingement studies on a flat plate: flow separation of laminar boundary layers
Publisher: Cambridge University Press (CUP)
Date: 04-11-2022
DOI: 10.1017/JFM.2022.827
Abstract: Interactions between shock waves and boundary layers produce flow separations and augmented pressure/thermal loads in hypersonic flight. This study provides details of Mach 7 impinging-shock-flat-plate experiments conducted in the T4 Stalker Tube. Measurements were taken at flow conditions of Mach 7.0 (2.44 MJ kg $^{-1}$ ) and Mach 7.7 (2.88 MJ kg $^{-1}$ ) flight enthalpies with a range of freestream unit Reynolds numbers from $1.43 \\times 10^{6}$ m $^{-1}$ to $5.01 \\times 10^{6}$ m $^{-1}$ . A shock generator at $12^{\\circ }$ or $16^{\\circ }$ to the freestream created an oblique shock which impinged on a boundary layer over a flat plate to induce flow separation. The flow field was examined using simultaneous measurements of wall static pressure, heat transfer and schlieren visualisation. Measured heat transfer along the flat plate without the shock impingement indicated that the boundary layer remained laminar for all flow conditions. The shock impingement flow field was successfully established within the facility test duration. The onset of separation was observed by a rise in wall pressure and a decrease in heat transfer at the location corresponding to the stem of the separation shock. Downstream of this initial rise, an increased pressure and higher heating loads were observed. The heat-transfer levels also indicated an immediate boundary layer transition due to the shock impingement. The separation data of the present work showed good agreement with our previous work on shock impingement on heated walls (Chang et al. , J. Fluid Mech. , vol. 908, 2021, pp. 1–13). A comparison with the previous scaling indicated that the separation also relates to the pressure ratio and the wall temperature parameter.
Holographic digital Fourier microscopy for selective imaging of biological tissue
Publisher: Wiley
Date: 2004
DOI: 10.1002/IMA.20031
Dynamic visualization of line integrals of vector fields: a didactic proposal
Publisher: Informa UK Limited
Date: 21-08-2018
Experimental Expansion Tube Study of the Flow over a Toroidal Ballute
Publisher: American Institute of Aeronautics and Astronautics (AIAA)
Date: 09-2004
DOI: 10.2514/1.13104
Analysis of Nonequilibrium CN Radiation Encountered During Titan Atmospheric Entry
Publisher: American Institute of Aeronautics and Astronautics (AIAA)
Date: 10-2011
DOI: 10.2514/1.50966
Dynamic e-learning modules for student lecture preparation.
Publisher: International Society for the Scholarship of Teaching and Learning
Date: 20-03-2018
Carbon Ablation in Hypervelocity Air and Nitrogen Shock Layers
Publisher: American Institute of Aeronautics and Astronautics (AIAA)
Date: 04-2018
DOI: 10.2514/1.T5270
Dual/scram-mode combustion limits of ethylene and surrogate endothermically-cracked hydrocarbon fuels at Mach 8 equivalent high-enthalpy conditions
Publisher: Elsevier BV
Date: 2021
A method for achieving super-resolved widefield CARS microscopy
Publisher: The Optical Society
Date: 26-08-2010
DOI: 10.1364/OE.18.019263
Upstream porthole injection in a 2-D scramjet model
Publisher: Springer Science and Business Media LLC
Date: 04-2002
Experimental Analysis of the Interaction of Carbon and Silicon Ablation Products in Expanding Hypersonic Flows
Publisher: American Institute of Aeronautics and Astronautics
Date: 15-09-2018
DOI: 10.2514/6.2018-5325
Visible and Near Infrared Spectroscopy of Hayabusa Reentry Using Semi-Autonomous Tracking
Publisher: American Institute of Aeronautics and Astronautics (AIAA)
Date: 2014
DOI: 10.2514/1.A32497
Expansion Tunnel Experiments of Earth Reentry Flow with Surface Ablation
Publisher: American Institute of Aeronautics and Astronautics (AIAA)
Date: 09-2016
DOI: 10.2514/1.A33267
Numerical Modeling of Earth Reentry Flow with Surface Ablation
Publisher: American Institute of Aeronautics and Astronautics (AIAA)
Date: 2016
DOI: 10.2514/1.A33266
Fundamental Scramjet Combustion Experiments using Hydrocarbon Fuel
Publisher: American Institute of Aeronautics and Astronautics
Date: 15-09-2018
DOI: 10.2514/6.2018-5201
Expansion Tube Test Flow Design for Magnetohydrodynamic Aerobraking
Publisher: American Institute of Aeronautics and Astronautics (AIAA)
Date: 04-2021
DOI: 10.2514/1.J058389
Carbon Ablative Shock-Layer Radiation with High Surface Temperatures
Publisher: American Institute of Aeronautics and Astronautics (AIAA)
Date: 2017
DOI: 10.2514/1.T4902
Visualization and analysis of bow shocks in a superorbital expansion tube
Publisher: American Institute of Aeronautics and Astronautics (AIAA)
Date: 10-1996
DOI: 10.2514/3.13376
Ionizing Nitrogen and Air Flows in a Superorbital Expansion Tube
Publisher: American Institute of Aeronautics and Astronautics (AIAA)
Date: 09-2000
DOI: 10.2514/2.1154
Vacuum Ultraviolet Spectral Measurements for Superorbital Earth Entry in X2 Expansion Tube
Publisher: American Institute of Aeronautics and Astronautics (AIAA)
Date: 12-2015
DOI: 10.2514/1.J054027
Fringe—A Java-based finite fringe analysis package
Publisher: Elsevier BV
Date: 09-2012
Optical and Pressure Measurements in Shock Tunnel Testing of a Model Scramjet Combustor
Publisher: American Institute of Aeronautics and Astronautics (AIAA)
Date: 05-1997
DOI: 10.2514/2.5196
Magnetohydrodynamic Drag Force Measurements in an Expansion Tube
Publisher: American Institute of Aeronautics and Astronautics
Date: 24-06-2018
DOI: 10.2514/6.2018-3755
Simulating Gas Giant Atmospheric Entry Using Helium and Neon Test Gas Substitutions
Publisher: American Institute of Aeronautics and Astronautics (AIAA)
Date: 05-2019
DOI: 10.2514/1.A34282
Study of hypervelocity non equilibrium flows in impulse facilities
Publisher: American Institute of Aeronautics and Astronautics
Date: 09-01-2012
DOI: 10.2514/6.2012-726
Expansion Tube Magnetohydrodynamic Experiments with Argon Test Gas
Publisher: American Institute of Aeronautics and Astronautics
Date: 24-06-2018
DOI: 10.2514/6.2018-3754
Near-resonant holographic interferometry and absorption measurements of seeded atomic species in a flame
Publisher: Optica Publishing Group
Date: 19-11-0019
DOI: 10.1364/AO.43.003391
Abstract: The development of near-resonant holographic interferometry techniques for use on flows seeded with atomic species is described. A theoretical model for the refractivity that is due to the seed species is outlined, and an approximation to this model is also described that is shown to be valid for practical regimes of interest and allows the number density of the species to be determined without knowledge of line-broadening effects. The details of quantitative number density experiments performed on an air-acetylene flame are given, and a comparison with an alternative absorption-based experiment is made.
Comparison of Titan Entry Radiation Shock-Tube Data with Collisional-Radiative Models
Publisher: American Institute of Aeronautics and Astronautics (AIAA)
Date: 2010
DOI: 10.2514/1.T4231
Superorbital expansion tube tests of a caret waverider
Publisher: Springer Science and Business Media LLC
Date: 08-2007
Boundary Layers on a Flat Plate at Sub- and Superorbital Speeds
Publisher: American Institute of Aeronautics and Astronautics (AIAA)
Date: 10-2007
DOI: 10.2514/1.26894
Detecting shock arrival in expansion tubes and shock tunnels using high-frequency photodiodes
Publisher: Springer Science and Business Media LLC
Date: 06-2021
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