• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.04a
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• pp.77-78
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• 2011

A multi-step quasi-global mechanism is developed for the kerosene/oxygen combustion analysis including dissociation products. Reaction constants of the global reaction are determined to have agreement with experimental data. The mechanism is used for the numerical analysis of the combustion flow field of the kerosene/oxygen shear coaxial injector. The results from high-resolution numerical analysis confirmed qualitatively that the recess enhance the fuel/air mixing and combustion efficiency by the increased flow instabilities.

• Journal of computational fluids engineering
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• v.11 no.3 s.34
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• pp.22-27
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• 2006

Flow around a guided missile in high maneuver, i.e. at a high angle of attack, shows complex phenomena. It is well known that even in geometrically symmetric conditions the flow around a missile at high angles of attack can generate unexpected large side forces and yaw moments due to asymmetric vortices. In this paper, a CFD code (FLUENT) based on the Navier-Stokes equations was used for the numerical analysis to find a suitable numerical mechanism for generation of asymmetric vortices. It is shown that a numerical technique of applying different surface roughness to a specific area of the missile nose surface gives the best fit in comparison with the experimental results. In addition, a numerical investigation of variations of side forces and pressure distributions with angle of attack and roll angle was conducted for the purpose of identifying the source of vortex asymmetries.

• Journal of the Korean Society of Propulsion Engineers
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• v.24 no.4
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• pp.25-32
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• 2020

A numerical study on combustion instabilities in a model combustor was conducted with various momentum flux ratios. Five ratios are calculated based on an actual operating condition of rocket engine. As momentum flux ratio increases, the spreading angle on the injector outlet decreases. And, as increase of axial momentum flux, pressure fluctuation decreases inside the combustor. By using dynamic mode decomposition method, the acoustic modes inside the combustor are identified. Combustion stabilities are analyzed by comparing the damping coefficient of the 2^nd longitudinal mode.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.38 no.6
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• pp.493-500
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• 2014

Nonlinear characteristics of cellular counterflow diffusion flame near the radiative extinction limit at large Damk$\ddot{o}$hler number are numerically investigated. Lewis number is assumed to be 0.5 and flame evolution is calculated by imposing an infinitesimal disturbance to a one-dimensional(1-D) steady state flame. The early stage of nonlinear development is very similar to that predicted in a linear stability analysis. The disturbance with the wavenumber of the fastest growing mode emerges and grows gradually. Eventual, an alternating pattern of reacting and quenching stripes is developed. The cellular flame temperature is higher than that of 1-D flame because of the gain of the total enthalpy. As the Damk$\ddot{o}$hler number is further increased, the shape of the cell becomes circular to increase the surface area per unit reacting volume. The cellular flames do not extinguish but survive even above the 1-D steady state extinction condition.

• Journal of the Korean GEO-environmental Society
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• v.10 no.7
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• pp.81-91
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• 2009

Recently, twin-tunnel is often designed in the aspects of disaster prevention and economical reasons. However, the design cases and the studies are relatively insufficient. By the twin-tunnel excavation, deviate stresses of pillar between tunnels are increased and the increased stresses induce the instability of the twin-tunnel. In this study, numerical analyses about the twin-tunnel behaviour were conducted with varying ground strength, width of pillar and depth of earth cover and a series of regression analyses were carried out by using the results of numerical analyses for the twin-tunnel. Based on the numerical analyses, an estimation method of derived stresses is suggested through the regression analyses. Also, based on the results of regression analyses, an quantitative estimation method considering the reinforcement effects is also suggested. Then various parametric studies were conducted to be considered the reinforcement type and various design parameters. Finally, the efficiency of the suggested method based on the Hoek-Brown Failure Criterion is verified through the results of parametric studies.

• The Journal of Korean Institute of Electromagnetic Engineering and Science
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• v.13 no.5
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• pp.475-483
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• 2002

The new architecture for the stabilization of an adaptive linearizer using the RLS algorithm is presented. The delay lock loop is apl)lied to compensate the feedback loop delay of the nonlinear amplifier output, and the Yang's algorithm is used to mitigate the numerical unstability of the RLS algorithm. This method is applied to the linearizer using the polynomial predistorter, and it's efficacy is verified by the simulation of the proposed structure.

• Proceedings of the KIEE Conference
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• 2009.07a
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• pp.1406_1407
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• 2009

Fowler-Nordheim의 전자 방출과 열전자 방출 메카니즘을 이용하여 절연유체 내 전계에 의한 도체의 음극에서 전자 방출현상과 열에 의한 열전자 방출현상을 고려하고 유한요소법(Finite Element Method)을 이용하여 해석하였다. 절연유체 내 공간전하에 대한 해석기법으로 푸아송 방정식, 양이온, 음이온, 전자에 대한 전하연속 방정식, 온도에 대한 열 확산 방정식으로 이루어진 5개의 지배방정식에 Fowler-Nordheim의 전계 방출과 Richardson-Dushman의 열전자 방출을 경계조건으로 부여하였다. 단자 전류는 유한요소법과 잘 부합하는 에너지법으로 계산되었다. 쌍 곡선형 PDE의 공간전하 전파에 대한 지배 방정식은 일반적으로 수치적인 불안정성을 가지므로 인공 확산 항을 고려하여 이를 해결하였다. 제안된 해석법은 세 개의 캐리어를 가진 x-y 좌표축의 2차원 평판 모델에 적용하여 그 유효성을 확인하였다.

• Journal of the Korean Society of Surveying, Geodesy, Photogrammetry and Cartography
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• v.20 no.2
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• pp.155-164
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• 2002

In this study, in order to discuss the geometric correction methods of high-resolution IKONOS satellite image, the existing polynomial model and RFM which is able to rectify satellite image without auxiliary data are applied to IKONOS satellite image data. Then the accuracy of ground point versus number of GCPs and each order of RFM are assessed. A numerical instability is removed by application of Tikhonov regularization method. As the results of this study, the root mean square errors of RFM is decreased more than 2 pixels in comparison with the two dimensional polynomial model.

• KSCE Journal of Civil and Environmental Engineering Research
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• v.14 no.5
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• pp.1105-1113
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• 1994

For the design of various structures, the dynamic analysis of the structures is essential. Eigenproblem must be first computed when the mode superposition method is used in the dynamic analysis of the structures. However, since most of solution time is spent on calculating the eigenpairs of the system, the development of more efficient solution method is required. The purpose of this paper is to present the efficient solution method that combines the Robinson-Lee's method and accelerated Newton-Raphson method to improve numerical stability and increase convergence. Effectiveness of the proposed method is verified through numerical examples.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.30 no.6
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• pp.14-20
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• 2002

The aerodynamic heating at a nose cone is predicted under the KSR-III flight conditions. An equilibrium reacting gas condition is applied. The parametric study is performed with Mach number of 4.9, 10.2 and 15 and for the following nose shapes of hemisphere, cut cylinder and parabola. AUSMPW+ and shock aligned grid technique are used to provide the best aerodynamic solutions. In addition, the composite material of a nose cone is discussed in the viewpoint of a thermal safety.