ORCID Profile
0000-0002-6590-3564
Current Organisation
University of Queensland
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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.
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 |
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
Publisher: Springer Science and Business Media LLC
Date: 03-2001
DOI: 10.1007/PL00004056
Publisher: American Institute of Aeronautics and Astronautics (AIAA)
Date: 06-1998
DOI: 10.2514/2.479
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.
Publisher: American Institute of Aeronautics and Astronautics (AIAA)
Date: 08-2016
DOI: 10.2514/1.J054659
Publisher: Elsevier BV
Date: 08-2020
Publisher: American Institute of Aeronautics and Astronautics (AIAA)
Date: 12-2000
DOI: 10.2514/2.916
Publisher: American Institute of Aeronautics and Astronautics (AIAA)
Date: 07-2010
DOI: 10.2514/1.J050207
Publisher: Springer Science and Business Media LLC
Date: 05-2018
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.
Publisher: Springer Science and Business Media LLC
Date: 07-2000
Publisher: American Institute of Aeronautics and Astronautics
Date: 05-01-2017
DOI: 10.2514/6.2017-0212
Publisher: American Institute of Aeronautics and Astronautics (AIAA)
Date: 12-2017
DOI: 10.2514/1.J056021
Publisher: Elsevier BV
Date: 03-2021
Publisher: Springer Science and Business Media LLC
Date: 28-02-2007
Publisher: Optica Publishing Group
Date: 15-06-2010
DOI: 10.1364/OE.18.014063
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.
Publisher: Elsevier BV
Date: 05-2018
Publisher: Cambridge University Press (CUP)
Date: 07-12-2020
DOI: 10.1017/JFM.2020.877
Publisher: American Institute of Aeronautics and Astronautics (AIAA)
Date: 06-1998
DOI: 10.2514/2.478
Publisher: Springer Science and Business Media LLC
Date: 10-1998
Publisher: American Institute of Aeronautics and Astronautics
Date: 24-06-2018
DOI: 10.2514/6.2018-4070
Publisher: Optica Publishing Group
Date: 28-09-2009
DOI: 10.1364/OL.34.002988
Publisher: American Institute of Aeronautics and Astronautics (AIAA)
Date: 11-2003
DOI: 10.2514/2.6833
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.
Publisher: American Institute of Aeronautics and Astronautics (AIAA)
Date: 04-2010
DOI: 10.2514/1.44482
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.
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.
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.
Publisher: Wiley
Date: 2004
DOI: 10.1002/IMA.20031
Publisher: Informa UK Limited
Date: 21-08-2018
Publisher: American Institute of Aeronautics and Astronautics (AIAA)
Date: 09-2004
DOI: 10.2514/1.13104
Publisher: American Institute of Aeronautics and Astronautics (AIAA)
Date: 10-2011
DOI: 10.2514/1.50966
Publisher: International Society for the Scholarship of Teaching and Learning
Date: 20-03-2018
Publisher: American Institute of Aeronautics and Astronautics (AIAA)
Date: 04-2018
DOI: 10.2514/1.T5270
Publisher: Elsevier BV
Date: 2021
Publisher: The Optical Society
Date: 26-08-2010
DOI: 10.1364/OE.18.019263
Publisher: Springer Science and Business Media LLC
Date: 04-2002
Publisher: American Institute of Aeronautics and Astronautics
Date: 15-09-2018
DOI: 10.2514/6.2018-5325
Publisher: American Institute of Aeronautics and Astronautics (AIAA)
Date: 2014
DOI: 10.2514/1.A32497
Publisher: American Institute of Aeronautics and Astronautics (AIAA)
Date: 09-2016
DOI: 10.2514/1.A33267
Publisher: American Institute of Aeronautics and Astronautics (AIAA)
Date: 2016
DOI: 10.2514/1.A33266
Publisher: American Institute of Aeronautics and Astronautics
Date: 15-09-2018
DOI: 10.2514/6.2018-5201
Publisher: American Institute of Aeronautics and Astronautics (AIAA)
Date: 04-2021
DOI: 10.2514/1.J058389
Publisher: American Institute of Aeronautics and Astronautics (AIAA)
Date: 2017
DOI: 10.2514/1.T4902
Publisher: American Institute of Aeronautics and Astronautics (AIAA)
Date: 10-1996
DOI: 10.2514/3.13376
Publisher: American Institute of Aeronautics and Astronautics (AIAA)
Date: 09-2000
DOI: 10.2514/2.1154
Publisher: American Institute of Aeronautics and Astronautics (AIAA)
Date: 12-2015
DOI: 10.2514/1.J054027
Publisher: Elsevier BV
Date: 09-2012
Publisher: American Institute of Aeronautics and Astronautics (AIAA)
Date: 05-1997
DOI: 10.2514/2.5196
Publisher: American Institute of Aeronautics and Astronautics
Date: 24-06-2018
DOI: 10.2514/6.2018-3755
Publisher: American Institute of Aeronautics and Astronautics (AIAA)
Date: 05-2019
DOI: 10.2514/1.A34282
Publisher: American Institute of Aeronautics and Astronautics
Date: 09-01-2012
DOI: 10.2514/6.2012-726
Publisher: American Institute of Aeronautics and Astronautics
Date: 24-06-2018
DOI: 10.2514/6.2018-3754
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.
Publisher: American Institute of Aeronautics and Astronautics (AIAA)
Date: 2010
DOI: 10.2514/1.T4231
Publisher: Springer Science and Business Media LLC
Date: 08-2007
Publisher: American Institute of Aeronautics and Astronautics (AIAA)
Date: 10-2007
DOI: 10.2514/1.26894
Publisher: Springer Science and Business Media LLC
Date: 06-2021
Start Date: 12-2022
End Date: 12-2025
Amount: $390,000.00
Funder: Australian Research Council
View Funded ActivityStart Date: 2010
End Date: 04-2013
Amount: $490,000.00
Funder: Australian Research Council
View Funded ActivityStart Date: 06-2020
End Date: 12-2023
Amount: $510,000.00
Funder: Australian Research Council
View Funded ActivityStart Date: 06-2015
End Date: 04-2018
Amount: $503,400.00
Funder: Australian Research Council
View Funded ActivityStart Date: 2012
End Date: 04-2015
Amount: $540,000.00
Funder: Australian Research Council
View Funded ActivityStart Date: 2013
End Date: 12-2015
Amount: $550,000.00
Funder: Australian Research Council
View Funded ActivityStart Date: 2007
End Date: 12-2010
Amount: $490,000.00
Funder: Australian Research Council
View Funded ActivityStart Date: 2016
End Date: 12-2016
Amount: $250,000.00
Funder: Australian Research Council
View Funded ActivityStart Date: 2004
End Date: 12-2009
Amount: $1,805,000.00
Funder: Australian Research Council
View Funded Activity