Open Access. Powered by Scholars. Published by Universities.®
- Publication Type
Articles 1 - 10 of 10
Full-Text Articles in Engineering
On The Interaction Of A Racing Car Front Wing And Exposed Wheel, S. Diasinos, G. Doig, T.J. Barber
On The Interaction Of A Racing Car Front Wing And Exposed Wheel, S. Diasinos, G. Doig, T.J. Barber
Aerospace Engineering
A numerical investigation of generic open-wheel racing car wing and wheel geometry has been conducted, using original sub-scale experimental data for validation. It was determined that there are three main interactions that may occur, identifiable by the path that the main and secondary wing vortices take around the wheel. Interaction ‘A’ occurs when the main and secondary wing vortices both travel outboard of the wheel; interaction ‘B’ is obtained when only the main wing vortex passes inboard of the wheel; while interaction ‘C’ sees both wing vortices travel inboard of the wheel. The different interactions are achieved when geometric changes …
Flow Compressibility Effects Around An Open-Wheel Racing Car, J. Keogh, G. Doig, S. Diasinos
Flow Compressibility Effects Around An Open-Wheel Racing Car, J. Keogh, G. Doig, S. Diasinos
Aerospace Engineering
A numerical investigation has been conducted into the influence of flow compressibility effects around an open-wheeled racing car. A geometry was created to comply with 2012 F1 regulations. Incompressible and compressible CFD simulations were compared-firstly with models which maintained Reynolds number as Mach number increased, and secondly allowing Mach number and Reynolds number to increase together as they would on track. Results demonstrated significant changes to predicted aerodynamic performance even below Mach 0·15. While the full car coefficients differed by a few percent, individual components (particularly the rear wheels and the floor/ diffuser area) showed discrepancies of over 10% at …
Investigation Of Conjugate Heat Transfer In Fluid-Structure Interaction Modeling Using Openfoam, Andrew Brown
Investigation Of Conjugate Heat Transfer In Fluid-Structure Interaction Modeling Using Openfoam, Andrew Brown
Aerospace Engineering
No abstract provided.
Transonic And Supersonic Ground Effect Aerodynamics, Graham Doig
Transonic And Supersonic Ground Effect Aerodynamics, Graham Doig
Aerospace Engineering
A review of recent and historical work in the field of transonic and supersonic ground effect aerodynamics has been conducted, focussing on applied research on wings and aircraft, present and future ground transportation, projectiles, rocket sleds and other related bodies which travel in close ground proximity in the compressible regime. Methods for ground testing are described and evaluated, noting that wind tunnel testing is best performed with a symmetry model in the absence of a moving ground; sled or rail testing is ultimately preferable, though considerably more expensive. Findings are reported on shock-related ground influence on aerodynamic forces and moments …
The Aerodynamics Of A Cornering Inverted Wing In Ground Effect, James Keogh, Graham Doig, Tracie J. Barber, Sammy Diasinos
The Aerodynamics Of A Cornering Inverted Wing In Ground Effect, James Keogh, Graham Doig, Tracie J. Barber, Sammy Diasinos
Aerospace Engineering
For racing car configurations an inverted wing produces negative lift that allows increased levels of acceleration to be maintained through corners. Routine aerodynamic analysis, however, will typically be in the straight-line condition. A numerical analysis of the inverted T026 wing geometry through the curved path of a constant radius corner was conducted. The asymmetrical properties of the oncoming flow resulted in the introduction of a rolling and yawing moment along the span, as well as side-force. Yaw angle, flow curvature and a velocity gradient resulted in changes to the pressure distribution over the wing surface. Primary vortex behaviour was observed …
Application Of Kriging To Motorsport Aerodynamic Analysis, Matthew Cruickshank, Graham Doig
Application Of Kriging To Motorsport Aerodynamic Analysis, Matthew Cruickshank, Graham Doig
Aerospace Engineering
Aerodynamic analysis in motorsport is conducted using three methods, computational, scaled experimental and full-scale operational. However, the varying fidelity, different sampling resolutions and unavoidable errors of each technique make valid comparisons between datasets from each method difficult and time consuming. Kriging is a geostatistical method to estimate values within a data field by examining and applying the trends of the dataset. This research examines how such techniques can be used to aid comparison between aerodynamic measurements of a race car. It examines how kriging can be used to transform discrete measurements, of varying fidelity and sampling resolution, into semi-continuous measurements, …
Computational Simulation Of An Altitude Adaptive Nozzle Concept, K. Schomberg, G. Doig, J. Olsen
Computational Simulation Of An Altitude Adaptive Nozzle Concept, K. Schomberg, G. Doig, J. Olsen
Aerospace Engineering
A computational analysis of an annular converging-diverging (CD) and an altitude adaptive expansion-deflection (ED) nozzle is presented. Numerical results were generated using a 2D axisymmetric, pressure-coupled solver in conjunction with the Spalart-Allmaras turbulence closure model and second order spatial discretisation schemes. Results were recorded over a theoretical altitude range and compared to experimental static pressure readings and schlieren images. The correlation between numerical and experimental static pressure values was high for all cases. Comparison of schlieren imagery outlined the large variety of flow regions within the ED nozzle flow field. The interactions between these regions were highly sensitive to turbulence …
Fundamental Studies Of Vortices Induced By A Vortex-Generator For Automotive Applications, Asiful Islam, Graham Doig
Fundamental Studies Of Vortices Induced By A Vortex-Generator For Automotive Applications, Asiful Islam, Graham Doig
Aerospace Engineering
For automotive applications, passive flow control devices can be used to reduce, delay or prevent flow separation. This study explores the nature of vortex generation and behaviour, numerically and experimentally, for a simple geometry at a Reynolds Number (Rex) of 5×105 and 1.945×106. The setup comprised a triangular vane vortex-generator mounted on a shallow ramp referenced from literature. Flow over the isolated ramp was validated with past experimental particle-image-velocimetry (PIV) data, which also highlighted the relative performance of various turbulence models. A parametric study was undertaken with the vane orientation defined by an angle-of-attack (β) and stream-wise location (xedge/xVG). These …
Aerodynamic Design And Development Of The Sunswift Iv Solar Racing Car, Graham Doig, Chris Beves
Aerodynamic Design And Development Of The Sunswift Iv Solar Racing Car, Graham Doig, Chris Beves
Aerospace Engineering
The aerodynamic design and development of the University of New South Wales' ultra-low-drag solar-electric Sunswitt IV car is described, detailing the student-led design process from initial concept sketches to the completed vehicle. The body shape was established and relined over a period of six months in 2008-2009, almost entirely using computational fluid dynamics. The guiding philosophy was that predictable handling and drag minimization in challenging, changing wind conditions of the type commonly seen during the World Solar Challenge across Australia was preferable to high performance only on 'perfect' days. The car won its class in the 2009 and 2011 World …
Implications Of Compressibility Effects For Reynolds-Scaled Testing Of An Inverted Wing In Ground Effect, G. Doig, Tracie J. Barber, Sammy Diasinos
Implications Of Compressibility Effects For Reynolds-Scaled Testing Of An Inverted Wing In Ground Effect, G. Doig, Tracie J. Barber, Sammy Diasinos
Aerospace Engineering
The influence of compressibility around an isolated inverted wing at a fixed Reynolds number was examined as relevant to the issue of wind tunnel scaling effects. Three-dimensional simulations were conducted for low ground clearances, at: full scale and a Mach number of 0.088, at 50% scale at Mach 0.176, and at 25% scale at Mach 0.352. As the scale was reduced, the increasing peak local Mach number between the wing and the ground resulted in a higher propensity of the flow to separate towards the trailing edge, and for incompressible or full-scale CFD to underestimate the lift and drag coefficients …