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Showing 10 out of a total of 22 results.
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Gas lensing in a heated spinning pipe
Mafusire, C
;
Forbes, A
;
Snedden, Glen C
;
Mahlase, Andrew CK
;
Michaelis, MM
;
Mathuthu, M
(
2006-07
)
Optical aberrations in a gas lenses
Mafusire, C
;
Forbes, A
;
Michaelis, MM
;
Snedden, Glen C
(
2010-08
)
Experimental results showing the internal three-component velocity field and outlet temperature contours for a model gas turbine combustor
Meyers, BC
;
Snedden, Glen C
;
Meyers, Bronwyn C
;
Roos, TH
;
Mahmood, GI
(
American Institute of Aeronautics and Astronautics
,
2011-09
)
Application of transition modelling in CFD for use with turbine blades
Dunn, Dwain I
;
Snedden, Glen C
;
Roos, T
;
Hildebrandt, T
(
American Institute of Aeronautics and Astronautics
,
2011-09
)
The design of a kerosene turbopump for a South African commercial launch vehicle
Snedden, Glen C
;
Smyth, J
;
Bindon, J
;
Brooks, M
;
Smith, G
(
AIAA 2012
,
2012-08
)
Characterisation of a refurbished 1½ stage turbine test rig for flowfield mapping behind blading with non-axisymmetric contoured endwalls
Snedden, Glen C
;
Roos, TH
;
Dunn, Dwain I
;
Gregory-Smith, D
(
American Institute of Aeronautics and Astronautics
,
2007-09
)
Turbulence model comparisons for a low pressure 1.5 stage test turbine
Dunn, Dwain I
;
Snedden, Glen C
;
Von Backström, TW
(
2009-09
)
Three-dimensional particle image velocimetry in a generic can-type gas turbine combustor
Meyers, BC
;
Snedden, Glen C
;
Meyers, Bronwyn C
;
Roos, TH
;
Mahmood, GI
(
American Institute of Aeronautics and Astronautics
,
2009-09
)
An overview of the turbopump development programme in the University of KwaZulu-Natal’s aerospace systems research group
Smyth, J
;
Philogene, L
;
Bindon, J
;
Brooks, M
;
Smith, G
;
Snedden, Glen C
(
2012-10
)
Optimisation of non-axisymmetric end wall contours for the rotor of a low speed, 1 1/2 stage research turbine with unshrouded blades
Bergh, J
;
Snedden, Glen C
;
Meyer, C
(
ASME publications
,
2012-06
)
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