http://publicationslist.org/data/con_doolan/atom.xml Con Doolanhttp://publicationslist.org/con_doolan$basepathfavicon.icoRecent additions to Con Doolan's PublicationsList.org pagehttp://publicationslist.org/publications.png2010-08-12T22:23:52Z http://publicationslist.org/con_doolan/refid42 2010-08-12T22:23:31Z

An ecient stochastic method is applied to the problem of mod- eling unsteady turbulent velocity uctuations within a turbulent at plate boundary layer. White noise is spatially and temporarily con- voluted by the time averaged Reynolds stress tensor and dissipation. The convolutions are conducted such that mean turbulent properties are reproduced and the spectral distribution of turbulent ...<br/><br/>R. F. Jones, C. J. Doolan and M. D. Teubner (2010) <i>ANZIAM Journal</i> 51: C541--554<br/>

http://publicationslist.org/con_doolan/refid43 2010-07-12T10:45:34Z

The performance of several novel hybrid RANS/LES methodologies for accurate flow and noise predictions of the NASA Tandem Cylinder Experiment are investigated. Simulations are performed using three different hybrid RANS/LES methodologies which employ different techniques to transform the baseline RANS model into a turbulence resolving subgrid scale model. The approaches investigated are the Scale-...<br/><br/>M. Weinmann, R. D. Sandberg and C. J. Doolan (2010) <i>16th AIAA/CEAS Aeroacoustics Conference, AIAA 2010-3787,</i> <br/>

http://publicationslist.org/con_doolan/refid41 2010-07-12T10:31:22Z

This paper investigates the unsteady, near wake of a circular cylinder in cross flow at a Reynolds number of 5.5 x 10^3 using Large Eddy Simulation (LES). The near and intermediate wake velocity fields and unsteady aerodynamic forces compare well against available experimental data. Flow visualisation results show the presence of intermittent Kelvin Helmholtz (KH) instabilities in the very near wa...<br/><br/>C.J.Doolan (2010) <i>Engineering Applications of Computational Fluid Mechanics (Accepted 31/5/2010)</i> : <br/>

http://publicationslist.org/con_doolan/refid40 2010-07-12T10:33:07Z

Zebb Prime, Ben Cazzolato and Con Doolan (2010) <i>Journal of Guidance, Control, and Dynamics </i> 33: 2 615-618<br/>

http://publicationslist.org/con_doolan/refid51 2010-07-12T23:54:06Z

The generation of aeolian tones by the interaction of a low Reynolds number, low Mach number flow with a rigid square cylinder attached to a rigid thin flat plate is numerically investigated. When the length of the plate is varied from L = 0:5D to 6D, where D is the side length of the square cylinder, the results can be grouped into three distinct regimes. For the first regime (L . D), the aeol...<br/><br/>Mohamed Sukri Mat Ali, Con J. Doolan and Vincent Wheatley (2010) <i>20th International Congress on Acoustics, ICA 2010</i> <br/>

http://publicationslist.org/con_doolan/refid44 2010-07-12T10:48:39Z

A sinusoidal modification to the leading edge of an airfoil (tubercles) has led to the elimination of tonal noise for a NACA 0021 airfoil at a Reynolds number, Re ~ 120,000. It has also been found that the overall broadband noise is reduced for a considerable range of frequencies surrounding the peak in tonal noise. Investigations have also revealed that changing the amplitude and spacing betw...<br/><br/>K. L. Hansen, R. M. Kelso and C.J. Doolan (2010) <i>16th AIAA/CEAS Aeroacoustics Conference, AIAA 2010-3700,</i> <br/>

http://publicationslist.org/con_doolan/refid45 2010-07-12T23:48:53Z

The aim of the present study is the assessment of advanced EASM turbulence models and hybrid RANS/LES methodologies for predicting the hydrodynamic eld of the NASA tandem cylinder conguration. Simulations are performed with the nite volume code OpenFOAM using a k-!-EASM model, a Partially-Integrated-Transport-Model (PITM) and a modied Flow-Simulation-Methodology (FSM). A grid convergence s...<br/><br/>M. Weinmann, R. D. Sandberg and C. J. Doolan (2010) <i>1st Workshop on Benchmark Problems for Airframe Noise Computations (BANC-I)</i> <br/>

http://publicationslist.org/con_doolan/refid50 2010-07-12T23:52:00Z

Elias J. G. Arcondoulis, Con J. Doolan, Anthony C. Zander and Laura A. Brooks (2010) <i>20th International Congress on Acoustics, ICA 2010</i> <br/>

http://publicationslist.org/con_doolan/refid49 2010-07-12T23:49:53Z

This paper presents an acoustic analysis of the noise generated at the trailing edge of a flat plate encountering low turbulence fluid flow. Experimental measurements were taken in an anechoic wind tunnel using four microphones: one mounted above the trailing edge, one below the trailing edge, one adjacent to the trailing edge and one above the leading edge. The noise spectra produced by the fl...<br/><br/>D.J. Moreau, M.R. Tetlow, L.A. Brooks and C.J. Doolan (2010) <i>20th International Congress on Acoustics, ICA 2010</i> <br/>

http://publicationslist.org/con_doolan/refid48 2010-07-12T23:47:52Z

A new computational aeroacoustic model suitable for the prediction of turbulent airfoil trailing edge noise is presented. The method (known as the RANS based Statistical Noise Model or RSNM) combines numerically generated, mean turbulence information with a Green's function for a semi-infinite half-plane to generate a far-field acoustic auto-spectrum. As a preliminary application of the method, t...<br/><br/>C.J. Doolan, C. Albarracin Gonzalez and C. H. Hansen (2010) <i>20th International Congress on Acoustics, ICA 2010</i> <br/>

http://publicationslist.org/con_doolan/refid46 2010-08-12T22:21:52Z

A new method for calculating the aerodynamic noise generated by bluff bodies is presented in this paper. The methodology uses two-dimensional, Unsteady Reynolds Averaged Navier Stokes turbulent flow simulations to calculate the acoustic source terms. To account for turbulent flow effects that are not resolved by the flow simulation, a statistical approach has been developed and applied to introd...<br/><br/>C.J. Doolan (2010) <i>Applied Acoustics (Accepted 12/8/2010)</i> : <br/>

http://publicationslist.org/con_doolan/refid47 2010-07-12T23:45:34Z

Flows over a square cylinder of side length D with and without a splitter plate at a Reynolds number of 150 is numerically investigated. The length of the splitter plate is varied systematically from L = 0.5D to L = 6D so the sensitivity of the flow structure to the inclusion of the splitter plate can be inspected. It is found that the splitter plate introduces a strong hydrodynamic interactio...<br/><br/>Mohamed Sukri Mat Ali, Con J. Doolan and Vincent Wheatley (2010) <i>Physics of Fluids (Under Review)</i> : <br/>

http://publicationslist.org/con_doolan/refid28 2010-07-12T10:50:17Z

A theoretical, experimental and numerical study is presented of the interaction of a vortex wake created by an upstream blade with a downstream prismatic block. The aim of the study is to investigate the fundamentals of force and noise generation for this type of flow and explain how inter-object spacing affects the far-field noise level. A theoretical model, based on a compact form of Curle's f...<br/><br/>C. Doolan, D. Leclercq (2009) <i>Journal of Fluids and Structures</i> 25: 5 867-888<br/>

http://publicationslist.org/con_doolan/refid35 2009-01-26T06:39:33Z

Boyd, M, Doolan, C, Kestell, C (2009) <i>International Advanced Mobility Forum (IAMF),10th - 12th March 2009</i> <br/>

http://publicationslist.org/con_doolan/refid33 2009-01-26T21:54:35Z

BLUFF bodies are integral components of aircraft, high-speed trains, automobiles, and many forms of industrial equipment. The minimization of mean and fluctuating force levels generated by bluff bodies when placed in a fluid stream has the benefits of reducing drag, vibration, and radiated sound. It is therefore very important that a good understanding of the flowfield about bluff bodies be o...<br/><br/>Con. J. Doolan (2009) <i>AIAA Journal</i> 47: 2 475-479<br/>

http://publicationslist.org/con_doolan/refid37 2009-06-25T23:48:15Z

This paper describes a systematic method of refining a computational grid for the Direct Numerical Simulation (DNS) of flow about a square cylinder. The grid refinement method involves two stages. The first stage constructs computational meshes based on reasonable estimates of cell size and grid stretching ratios and investigates the sensitivity of the computed flow field to these parameter...<br/><br/>Mohamed Sukri Mat Ali, Con J. Doolan and Vincent Wheatley (2009) <i>Proceedings of the Seventh International Conference on CFD in the Minerals and Process Industries</i> <br/>

http://publicationslist.org/con_doolan/refid38 2009-06-25T23:52:01Z

The NASA Tandem Cylinder experiment has been simulated for the case where the cylinders were placed 3.7 diameters apart (center-to-center). This configuration allows vortex shedding to occur in the inter-gap region between the cylinders. Two-dimensional, unsteady Reynolds averaged Navier Stokes flow simulations were performed using the OpenFOAM open source code. Simulated mean and unsteady flow r...<br/><br/>Con Doolan (2009) <i>15th AIAA/CEAS Aeroacoustics Conference</i> <br/>

http://publicationslist.org/con_doolan/refid39 2009-07-26T10:47:21Z

A computationally efficient, quasi-one-dimensional supersonic combustion ramjet (scramjet) propulsion model has been produced for use in hypersonic system design studies. The model solves a series of ordinary differential equations using a 4th order Runga-Kutta method, to describe the gas dynamics within the scramjet duct. Additional models for skin friction and wall heat transfer are also in...<br/><br/>Birzer, C. and Doolan, C.J. (2009) <i>Journal of Propulsion and Power (accepted 24/7/09)</i> : <br/>

http://publicationslist.org/con_doolan/refid34 2008-08-24T23:49:31Z

This paper will discuss a method of bluff body noise control that utilises the phenomenon of aerodynamic interference. This technique uses a second body (not necessarily bluff) that is placed in the wake of the bluff body whose noise we wish to control. Through proper understanding of the wake dynamics, the amplitude and phase of the noise from the downstream body can be controlled so as to achi...<br/><br/>Con Doolan (2008) <i>Australian Institute of Physics (AIP), 18th National Congress (SUBMITTED), 30 November - 5 December 2008, Adelaide, South Australia</i> <br/>

http://publicationslist.org/con_doolan/refid32 2008-06-23T19:02:34Z

The fluid dynamics and acoustic emission that occurs when a flat plate is placed in the near wake of a square cylinder has been studied numerically. First, a two-dimensional direct numerical simulation (DNS) about a single square cylinder at $Re=150$ was performed and validated against available experimental and numerical data. Using an analytical model of sound generation and DNS data, the opti...<br/><br/>Con Doolan (2008) <br/>

http://publicationslist.org/con_doolan/refid29 2008-04-08T00:11:44Z

If technology such as aircraft, submarines and wind turbines are to further reduce their noise emissions, then a better understanding of airfoil trailing edge noise is required. This paper will discuss the physical causes of trailing edge noise and then review the methodologies used over the past couple of decades to model and estimate TE noise. A comprehensive reference list is given for reader...<br/><br/>C.J. Doolan (2008) <i>Acoustics Australia (Accepted, April)</i> : <br/>

http://publicationslist.org/con_doolan/refid31 2008-02-19T03:51:01Z

A theoretical description of a fuel-air mixing loss model is derived from first principles and placed within a quasi-one-dimensional scramjet combustor code. This code is then compared with experimental and multidimensional computational fluid dynamics results from the literature. Quasi-one-dimensional results compare well against published data and show that this approach is suitable for concept...<br/><br/>Doolan, C. and Boyce, R. (2008) <i>15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, AIAA-2008-2603</i> <br/>

http://publicationslist.org/con_doolan/refid30 2008-08-12T04:11:32Z

Prime, Z., Cazzolato, B. and Doolan, C. (2008) <i>AIAA Guidance, Navigation and Control Conference, Honolulu, Hawaii, AIAA-2008-6787</i> <br/>

http://publicationslist.org/con_doolan/refid5 2007-08-24T05:21:22Z

A computationally efficient, quasi-one-dimensional supersonic combustion ramjet propulsion model has been produced for use in hypersonic system design studies. The model uses a series of ordinary differential equations, solved using a 4th order Runge-Kutta method, to describe the gas dynamics within the scramjet duct. Additional models for skin friction and wall heat transfer are also included. ...<br/><br/>Cristian Birzer and Con J. Doolan (2007) <i>Proceedings of the 18th AIAA CFD Conference</i> <br/>

http://publicationslist.org/con_doolan/refid6 2007-08-24T07:17:54Z

The interaction of a helicopter’s main rotor tip vortex with the tail rotor is an important source of noise and vibration, yet it is still poorly understood. An important limiting case is the orthogonal blade vortex interaction (OBVI) where a three-dimensional vortex structure is cut by the tail rotor blade. It has been discovered that the blade unsteady surface pressures during OBVI are contr...<br/><br/>Con J. Doolan and Damien Leclercq (2007) <i>Proceedings of the 6th Australian Vertiflite Conference on Helicopter Technology</i> <br/>

http://publicationslist.org/con_doolan/refid10 2007-08-24T07:42:41Z

This paper compares the performance of the scramjet powered stages of two different launch systems; one using a hydrogen fuelled scramjet stage and one using a hydrocarbon fuelled scramjet stage. The two launch systems are optimized with respect to payload delivery capability and then compared, assuming a fixed launch mass. A rocket powered booster is used to achieve the required scramjet ignition...<br/><br/>M. R. Tetlow and C. J. Doolan (2007) <i>Journal of Spacecraft and Rockets</i> 44: 2 365-373<br/>

http://publicationslist.org/con_doolan/refid4 2007-08-24T07:23:30Z

A potential flow and viscous flow solver have been coupled to produce a robust computational tool useful for the design of low speed wind tunnel contractions. A validation study was successfully performed and it is shown that the computational model compares favorably with experimental and numerical results from the literature. The flow solver was then used in a numerical optimization methodolog...<br/><br/>Con J. Doolan and Rick C. Morgans (2007) <i>Proceedings of the 18th AIAA CFD Conference</i> <br/>

http://publicationslist.org/con_doolan/refid7 2007-08-24T07:27:16Z

After more than half a century of intense activity and the considerable development of complex numerical models, aeroacoustic research still relies heavily on experimental approaches. Experimental data is essential to provide reference data for fundamental test cases, to understand highly complex and interacting phenomena, and to validate numerical simulations. At the University of Adelaide, t...<br/><br/>Damien Leclercq, Con Doolan and Jochen Reichl (2007) <i>Proceedings of the 14th International Congress on Sound and Vibration</i> <br/>

http://publicationslist.org/con_doolan/refid1 2008-01-30T22:43:04Z

A potential flow and viscous flow solver have been coupled to produce a robust computational tool useful for the design of low speed wind tunnel contractions. After validation against published numerical and experimental wind tunnel data, the method is used to evaluate recently proposed contraction shapes from the literature. The results show that, on balance, a 5th order polynomial provides a ...<br/><br/>Con J. Doolan (2007) <i>Journal of Fluids Engineering</i> 129: 9 1241-1244<br/>

http://publicationslist.org/con_doolan/refid11 2007-08-24T07:47:16Z

The performance of a conceptual, missile class, hypersonic vehicle was modeled using a 2 degree-of-freedom dynamics model. The vehicle was assumed to be air-launched, accelerated to a Mach number of 3 using a solid propellant rocket and subsequently propelled using a dual-mode scramjet engine to cruise at Mach numbers between 4 and 9. Modeling results show that fuel storage capacity and dynamic ...<br/><br/>Con J. Doolan (2007) <i>Journal of Spacecraft and Rockets</i> 44: 1 81-87<br/>

http://publicationslist.org/con_doolan/refid27 2007-11-14T21:10:46Z

The mixing of a passive scalar in the wake of a slightly heated cylinder has been studied numerically by coupling the Unsteady Reynolds Averaged Navier Stokes (URANS) equations with a scalar transport equation and a turbulent-scalar transport model for a Reynolds number of Re = 3900. The URANS method is shown to capture key features of the flow field and passive scalar fluctuations in the near w...<br/><br/>Con Doolan and J. Mi (2007) <i>Proccedings of the Australian Combustion Symposium</i> <br/>

http://publicationslist.org/con_doolan/refid25 2007-08-27T00:16:29Z

Leclercq, D., Doolan, C.J. (2007) <i>Proceedings of the 19th International Conference on Acoustics 2007</i> <br/>

http://publicationslist.org/con_doolan/refid3 2007-11-14T21:30:03Z

This work reports on the use of numerical optimisation techniques to optimise objective functions calculated by Computational Fluid Dynamics (CFD) simulations. Two example applications are described, the first being the shape optimisation of a low speed wind tunnel contraction. A potential flow and viscous flow solver have been coupled to produce a robust computational tool, with the contraction s...<br/><br/>R.C. Morgans, C.J. Doolan and D.W. Stephens (2007) <i>Proceedings of the 16th Australasian Fluid Mechanics Conference</i> <br/>

http://publicationslist.org/con_doolan/refid2 2007-11-14T21:29:05Z

The wake of a blunt airfoil has been analysed using a two-dimensional \underline{U}nsteady \underline{R}eynolds \underline{A}veraged \underline{N}avier \underline{S}tokes (URANS) method. The $k-\epsilon$, Spalart-Allmaras and \underline{P}artially \underline{R}esolved \underline{N}avier \underline{S}tokes (PRNS) turbulence models were compared along with experimental data. All three models were ...<br/><br/>Con J. Doolan (2007) <i>Proccedings of the 16th Australasian Fluid Mechanics Conference</i> <br/>

http://publicationslist.org/con_doolan/refid9 2007-08-24T07:38:08Z

This paper compares the performance of two different launch systems; one with a hydrogen fuelled scramjet stage and one with a hydrocarbon fuelled scramjet stage. The two launch systems are optimized with respect to payload delivery capability and then compared, assuming a fixed launch mass. A rocket powered booster is used to achieve the required scramjet ignition conditions and a rocket p...<br/><br/>M. R. Tetlow and C. J. Doolan (2006) <i>Proceedings of the 2006 IEEE/AIAA Aerospace Conference</i> <br/>

http://publicationslist.org/con_doolan/refid26 2007-08-27T00:21:23Z

A new performance model was developed for hydrocarbon fuelled (Jet A) scramjet powered hypersonic systems. It was applied to air-launched hypersonic missile concepts that were boosted to a specified Mach number (3) and dynamic pressure (40-100 kPa) using a solid propellant rocket motor. After boost, a dual-mode airbreathing supersonic ramjet engine accelerates the missile concept along a const...<br/><br/>Doolan, C.J. (2006) <i>Proceedings of the 44th Aerospace Sciences Meeting and Exhibit</i> <br/>

http://publicationslist.org/con_doolan/refid22 2007-08-27T00:07:02Z

This paper investigates the performance benefits of using scramjet propulsion to accelerate a second stage satellite launch vehicle to Mach 14. A two-stage solid rocket booster is used to achieve the required scramjet ignition conditions and another rocket stage is used to accelerate the payload from scramjet shut-down to orbital conditions. The lifting acceleration is used as a control parameter ...<br/><br/>Tetlow, M. and Doolan, C.J. (2005) <i>Proceedings of the 5th Australian Space Science Conference, </i> <br/>

http://publicationslist.org/con_doolan/refid8 2007-08-26T23:56:37Z

Modelling the complete chemical kinetics and flow physics of supersonic combustion is a complex task that requires considerable computational resources. To develop performance evaluation tools for future hypersonic vehicles, accurate yet computationally efficient solution methods are required. In this work, a supersonic flame model is derived and used in a quasi-one-dimensional internal flow...<br/><br/>Con J. Doolan (2005) <i>Proceedings of the 5th Asia-Pacific Conference on Combustion</i> <br/>

http://publicationslist.org/con_doolan/refid19 2007-08-26T23:58:11Z

Doolan, C.J. (2003) <i>Proceedings of the 2003 Australian Symposium on Combustion and the 8th Australian Flame Days</i> <br/>

http://publicationslist.org/con_doolan/refid12 2007-08-26T23:46:41Z

Wang, T., Doolan, C.J., Coton, F.N. and Galbraith, R.A.McD. (2002) <i>AIAA Journal</i> 40: 10 2037-2046<br/>

http://publicationslist.org/con_doolan/refid23 2007-08-27T00:09:17Z

Doolan, C.J. and Bateup, M. (2002) <i> Proceedings of the 2002 Symposium on Combustion and the Seventh Australian Flame Days pp: 93-97</i> 93-97<br/>

http://publicationslist.org/con_doolan/refid21 2007-08-27T00:00:32Z

Doolan, C.J. (2001) <i>Proceedings of the Fifth Australian Explosive Ordnance Symposium (Parari 2001)</i> <br/>

http://publicationslist.org/con_doolan/refid13 2007-08-26T23:48:13Z

Doolan, C.J. (90%), Coton, F.N. and Galbraith, R.A.McD. (2001) <i>Journal of the American Helicopter Society</i> : 1-7<br/>

http://publicationslist.org/con_doolan/refid20 2009-01-19T22:35:36Z

A multiple combustor pulse detonation engine concept is analysed using a fourteen species chemical equilibrium model. Results are coupled with an analytical two-dimensional supersonic inlet model to provide estimates of operational performance. The analysis provides preliminary engine sizing and operational information of hydrocarbon fuelled pulse detonation engines for future tactical missi...<br/><br/>Doolan, C.J. (2001) <i>Proceedings of the 14th Australasian Fluid Dynamics Conference</i> <br/>

http://publicationslist.org/con_doolan/refid14 2007-08-26T23:49:32Z

Doolan, C.J., Coton, F.N. and Galbraith, R.A.McD. (2001) <i>AIAA Journal</i> 39: 1 88-95<br/>

http://publicationslist.org/con_doolan/refid15 2007-08-26T23:51:23Z

Green, R.B., Doolan, C.J. and Cannon, R.M. (2000) <i>Experiments in Fluids</i> 29: 368-379<br/>

http://publicationslist.org/con_doolan/refid16 2007-08-26T23:53:39Z

Doolan, C.J., Coton, F.N. and Galbraith, R.A.McD. (1999) <i>The Aeronautical Journal</i> : 579-587<br/>

http://publicationslist.org/con_doolan/refid17 2007-08-26T23:54:41Z

Doolan, C.J. and Morgan, R.G. (1999) <i>Shock Waves</i> 9: 4 239-248<br/>

http://publicationslist.org/con_doolan/refid18 2007-08-26T23:55:55Z

Doolan, C.J. and Jacobs, P.A. (1996) <i>AIAA Journal34</i> 34: 6 <br/>

http://publicationslist.org/con_doolan/refid24 2007-08-27T00:10:47Z

Doolan, C.J. and Morgan, R.G. (1993) <i>Eighth National Space Engineering Symposium</i> <br/>