• 한국전산유체공학회:학술대회논문집
• /
• 2010.05a
• /
• pp.437-441
• /
• 2010

LES results of turbulent premixed combustion flows are introduced by using the dynamic sub-grid scale model based on G-equation describing the flame front propagation. The turbulent premixed combustion flows around bluff body and over backward facing step are analyzed to validate present formation. LES of swirling partially premixed combustion flame is also performed to conform the predictive capabilities of LES model and to prompt our understanding for the combustion flows over double cone swirl burner combustor by using CFD-ACE+ commercial code.

• 한국전산유체공학회:학술대회논문집
• /
• 2010.05a
• /
• pp.460-463
• /
• 2010

Ice accretion on aircraft surface can greatly impair the aerodynamic performance of aircraft. As an alternative to the traditional Lagrangian particle tracking approach, an Eulerian-based droplet impingement and ice accretion code for air flows containing water droplets was developed A CFD solver was also developed to solve the clean airflow. The results of present method were compared with experimental data and previous icing codes such as LEWICE and FENSAP-ICE and were confirmed to show good agreement each other in qualitative and quantitative ways.

• 한국전산유체공학회:학술대회논문집
• /
• 2010.05a
• /
• pp.93-98
• /
• 2010

One of the most effective key factors to improve performance of automotive reciprocating compressor is the design of suction and discharge reed valves. Reed valves are also the major sources of compressor noise. Valve motion is highly coupled with refrigerant flow. In this study, a process of fluid-structure interaction analysis was developed to predict the cylinder inner flow and the dynamic behavior of valve simultaneously. Interface programs computational structural dynamics code. The full cycle simulations of compressor were performed using FSI analysis was alidated by comparing the simulation results with the experimental results.

• 한국전산유체공학회:학술대회논문집
• /
• 2008.03a
• /
• pp.256-261
• /
• 2008

A CFD analysis of helicopter flowfield in forward flight is considered as non-trivial issue because of the complexity of vorticity-dominated flowfield. In this work, a study on the selection of the proper location for the installation of the Pitot probe is conducted using a CFD code which can deal with the interaction of rotor blade vortex and body. To describe the flow patterns for rotating rotor blades and body, the sliding mesh scheme is utilized. Pressure distributions and flow patterns are also analyzed to identify regions free from the interaction of body and wake induced from rotor blades.

• Proceedings of the KSME Conference
• /
• 2000.11b
• /
• pp.508-513
• /
• 2000

HANJUNG has developed demonstration plant treating combustion flue gas such as dioxide($SO_2$) and nitrogen oxides(NOx). Before operating this system, we tested the inner airflow characteristic of demonstration plant in the front of plasma reactor field 1 and field 2. The experimental results of $25,000Nm^3/hr$ airflow are compared with the computational results using FLUENT code. It is found that the velocity distribution trends are matched the experimental results with the calculation results. To improve the eccentric airflow in the inlet hood, it is necessary to install the vertical guide vane as well as the horizontal guide vane.

• 한국전산유체공학회:학술대회논문집
• /
• 2004.10a
• /
• pp.25-28
• /
• 2004

The purpose of this paper is to present essential numerical data of FCV(Flow rate Control Valve) which is used in a projectile ejection system for a underwater vehicle. A commercial CFD code is applied to analyze the 3 dimensional viscous compressible flow field within the FCV as four cases of opening rate, 25, 50, 75, and $100\%$. The flow coefficient of each cases are mainly calculated. And other characteristics such as the location of shock wave and total temperature distribution are also determined.

• 한국전산유체공학회:학술대회논문집
• /
• 2004.10a
• /
• pp.121-125
• /
• 2004

The preprocessor - solver - postprocessor software for 2D/Axisymmetric CSCM Upwind Flux Difference Splitting Navier-Stokes code has been developed for undergraduate educational purpose. This computational fluid dynamics (CFD) software allows students to setup, solve, visualize and control dynamically server for their own fluid problems via Internet. The preprocessor Is capable of generating geometry and grid, initial solution data and required solver control parameters. The postprocessor shows vector plot and contour plot with different options while residual plot shows root-mean-square (RMS) error history graphically and retrieves the data from solver interactively. Special feature of the preprocessor is grid generation part which is based on MFC/Visual C++ application and FORTRAN single block grid generator process. Many users can access solver via Internet from client computers and solve desired problems using locally installed pre- and postprocessor and remote powerful solver part.

• Journal of computational fluids engineering
• /
• v.11 no.4 s.35
• /
• pp.101-106
• /
• 2006

In the microfluidic devices the most important thing is mixing efficiency ol various fluids. In this study a newly designed miler is proposed to enhance the mixing effect with the purpose to apply it to microchannel mixing in a short future. This design is composed of a channel with cross baffles periodically arranged on the both bottom and top surfaces ol the channel. To obtain the yow patterns, the numerical computation was performed by using a commercial code, ANSYS CFX 10.0. To evaluate the mixing performance, we computed Lyapunov exponent and obtained Poincare sections. it was shown that our design provides the excellent mixing effect.

• 한국전산유체공학회:학술대회논문집
• /
• 2008.10a
• /
• pp.256-261
• /
• 2008

A CFD analysis of helicopter flowfield in forward flight is considered as non-trivial issue because of the complexity of vorticity-dominated flowfield. In this work, a study on the selection of the proper location for the installation of the Pitot probe is conducted using a CFD code which can deal with the interaction of rotor blade vortex and body. To describe the flow patterns for rotating rotor blades and body, the sliding mesh scheme is utilized. Pressure distributions and flow patterns are also analyzed to identify regions free from the interaction of body and wake induced from rotor blades.

• Journal of computational fluids engineering
• /
• v.15 no.4
• /
• pp.17-24
• /
• 2010

Using the numerical code for the interior ballistics, the performance of the interior ballistics with the characteristics according to the position of the solid propellant in chamber has been investigated. In existing research, propellants have been evenly distributed in the chamber. In this study, however, several cases of the existence of empty space in the chamber at which the propellants are not evenly distributed are considered. The 7-perforated propellant configuration has been used in this research. The results have shown the change of performance of the interior ballistics according to solid propellant positions in the chamber.