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Structure, Extinction & Ignition of Non-Premixed Flames in the Counterflow Configuration
Counterflow burners consist of steady, axisymmetric, laminar flows of two counterflowing reactant streams toward a stagnation plane. These burners can be used to experimentally study and develop detailed chemical mechanisms of combustion under a wide range of conditions. Global flame parameters such as the critical limits of extinction and autoignition, as well as flame structure, including flame temperatures and species concentrations can be measured and tested against established reaction mechanisms using 1D numerical model with known conditions at the duct exits. This presentation is a...
Reacting Flow Applications in STAR-CCM+
We have been expanding our application coverage for reacting flows that require coupling of different processes with a wide-range of length and time scales. We capture these interactions by using a combination of online as well as offline computations that enables us to perform advanced reacting flow calculations incorporating finite-rate chemistry while keeping the computational time manageable. Our models have been extended to work in multi-phase as well as with segregated and coupled flow solvers. Examples from chemical process and combustion applications will be shown that will include...
Integrating Filtration Mechanism with a 3D Diesel Particulate Filter (DPF) Model using STAR-CCM+
A 3D CFD model is developed for analysis of transient soot filtration processes in a conventional wall-flow type Diesel Particulate Filter (DPF). The primary objective of this study is to quantitatively predict the local values of soot filtration parameters, such as porosity, permeability, collection efficiency and deposited soot mass, within isotropically discretized computational domains in the multi-layered filter wall region. Standard CFD codes do not have ability to generate structured meshes with ordered cell index nor allow mathematical recursive operation using user field functions...
The Italian challenge at the Little America’s Cup 2013: Design and analysis method for the C Class prototypes
The Italian challenge at the Little America’s Cup 2013: Design and analysis method for the C Class prototypes
Welcome & Cervélo Keynote
Welcome & Cervélo Keynote
Experimental Validation of STAR-CCM+ for Liquid Container Slosh Dynamics
The NASA Launch Services Program has funded several propellant slosh related projects over the years with the goal of obtaining experimental data to anchor CFD predictions. STAR-CCM+ is used to create a CFD model of water sloshing in an 8” diameter spherical tank. The predictions from this CFD slosh model are compared to experimental data to validate the results. The data compared include slosh natural frequency, damping rate and free surface topology. These important validations allow us to increase our confidence in STAR-CCM+ for use on NASA missions.
An overview of battery simulation
An introduction to batteries is provided, including an overview of the commercial value of batteries sold by chemistry. Opportunities for battery simulation in various markets (automotive, consumer, industrial, etc.) are presented, along with examples of the STAR-CCM+ BSM module and Battery Design Studio.
CFD Study of an Industrial Heater
A CFD study using STAR-CCM+ 7.04 is performed to simulate an industrial heater with burners firing refinery gas fuel. The heater has been reported with short run length due to coking inside the process tubes. Heater, burners and combustion air duct are included in the modeled geometry. Turbulence, combustion and radiation models are activated to simulate the environment inside the heater. System analysis is performed such as combustion flame pattern, temperature and velocity fields, heat flux and temperature distribution at various locations etc. Non-uniform heat flux distribution on process...
Optimate Evaluation: Design Optimization of a Generic Glider
One of the difficulties of optimization of any design using CFD is the sheer number of runs required using traditional methods. This presentation details the use of Optimate for the optimization of a generic glider. This case was designed to stress the SHERPA algorithm with a realistically complex set of design criteria to optimize an aerodynamic vehicle, including stability requirements and trimmed L/D performance requirements.