• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2005.11a
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• pp.201-206
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• 2005

The effect of internal liquid flow on spray plume characteristics was performed experimentally in subsonic crossflows. The injector internal flow was classified as three modes such as a normal, cavitation, and hydraulic flip. The objectives of the research are to investigate the effect of internal liquid flow on the spray plume characteristics and compare the trajectory of spray plume with previous works. The results suggest that the trajectory of spray plume can be correlated as a function of liquid/air momentum flux ratio(q), injector diameter and normalized distance from the injector exit(x/d). It's also found that the injector internal turbulence influences the spray plume characteristics significantly.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.04a
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• pp.229-232
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• 2007

하이브리드 로켓의 연소율을 높이기 위해 유동 특성을 바꾸면서 실험을 수행하였고 연소된 연료 내부 표면이 고르지 못한 것을 볼 수 있었다. 그 원인을 밝히기 위해 연료 표면을 관찰하고 유동가시화 실험을 한 결과 거친 연료 표면의 원인이 검댕 때문이고 이것은 국부적인 산화제 부족현상 때문에 발생하게 되었다는 것을 알 수 있었다. 또 연소 시 연료 전체에 발생하는 검댕의 특성은 이 현상이 하이브리드 로켓만의 독특한 특징인 분출효과 때문이라고 예측할 수 있게 해주었다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.11a
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• pp.300-303
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• 2010

The present study investigates the flow characteristics of simulant gel propellant(carbopol 0.5%wt) in a variety of injectors. Rheological data for gel propellant has been measured and injector flow characteristics for plain-orifice, chamfered-orifice and venturi type injector have been numerically analyzed. The apparent viscosity of plain-orifice and chamfered-orifice have tendency to increase along axial direction, whereas for venturi type injector, low viscosity has been achieved in the injector flow. This phenomenon was clearly pronounced as Reynolds number is increased.

• Journal of the Korean Society of Propulsion Engineers
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• v.4 no.4
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• pp.70-77
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• 2000

Supersonic Dual Bell Nozzle (SDBN) is an altitude-adaptive propulsion nozzle achieved only by a nozzle wall inflection. In order to investigate the altitude adaptive capability and the effectiveness of this nozzle concept, the present study addresses a computational work of the flow through SDBN. Several types of the SDBNs are tested for a wide range of the pressure ratio which covers from an over-expended flow to a fully under-expended flow at the exit of the SDBN. Axisymmetric, compressible, Wavier-Stokes equations are numerically solved using a fully implicit finite volume differencing scheme. The present computational results reveal that the base nozzle length affects the shock wave system occurring inside SDBN. For a quit wide range of the pressure ratio the flow separation occurs at the nozzle inflection point. It is found that the maximum thrust coefficient is obtainable for the correct expansion state at the exit of SDBN.

• Proceedings of the Korea Society for Energy Engineering kosee Conference
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• 1996.04a
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• pp.44-48
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• 1996

본 연구는 석탄가스화복합발전(IGCC) 시스템중 핵심 단위 장치중의 하나인 가스화기 내부에서 일어나는 석탄의 가스화 반응 연구를 PCGC-2 프로그램을 통해 수행하였으며 일차적인 목표로 반응장에서의 선회 강도에 따른 가스화기내 유동 및 반응 특성을 파악하고자 하였다.

• Transactions of the Korean Society of Mechanical Engineers A
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• v.35 no.12
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• pp.1627-1633
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• 2011

Injection molds are generally fabricated by assembling a number of plates in which the core and cavity components are assembled. This assembled structure has a number of contact interfaces where the heat transfer characteristics are affected by thermal contact resistance. In previous studies, numerical approaches were investigated to predict the effect of thermal contact resistance on the temperature distribution of injection molds. In this study, thermal-fluid coupled numerical analyses are performed to take into account the thermal contact effect on the numerical evaluation of the mold filling characteristics. Comparisons with experimental results show that the proposed coupled analysis provides more reliable results than the conventional analyses in predicting the mold filling characteristics by taking into account the effect of thermal contact resistance inside the injection mold assembly.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.31 no.2
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• pp.10-16
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• 2003

The unsteady supersonic flow over tandem cavities has been analyzed by the integration of Navier-Stokes equations with the k-$\varepsilon$ turbulence model. The unsteady flow is characterized by the periodicity due to the mutual relation between the shear layer and the internal flow in cavities. The upwind TVD scheme based on the flux vector split with the van Leer limiters is used. The results show the principal frequency is very reasonable. The principal frequency of the rear cavity due to the front cavity has been analyzed by the combination of the several aspect ratios of cavities. In the case of the front cavity of low aspect ratio, the frequencies of tandem cavities are almost same, because two shear layers developed from each cavity are mixed and developed to one shear layer. However, in the case of the front cavity of high aspect ratio, the characteristis of frequency are very different, because the second shear layer is developed in the diffused first shear layer.

• Proceedings of the KSME Conference
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• 2005.11a
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• pp.83.2-83.2
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• 2005

• Journal of the Korea Academia-Industrial cooperation Society
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• v.19 no.11
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• pp.513-520
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• 2018

This research concerns the characteristics of tank barrel inner flow according to the barrel length and the pressure of ammunition when fired. By analyzing the flow characteristics of the bore evacuator according to barrel length and ammunition pressure regarding ammunition design, it is possible to prevent the flareback phenomenon that may occur during ammunition operation. Through bore evacuator flow analysis by barrel length and ammunition pressure, we identified key design factors concerning barrel and ammunition compatibility including speed, accuracy, penetration performance and range. Test results found if barrel length is long and ammunition pressure is low, bore evacuator operation time is slow. Therefore, there is a high probability that propellant gas will enter the battle vehicle. Therefore, the correlation analysis method of bore evacuator flow characteristics based on barrel length and ammunition pressure is considered as a primary method to improve operational performance. When designing new ammunition, the correlation analysis method will be used to determine ammunition weight and select the propellant pressure.

• Journal of the Korean Society of Propulsion Engineers
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• v.13 no.6
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• pp.48-55
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• 2009

The purpose of using Gas Generator Oxidizer On/Off Valve(GOV) is to control opening and closing of oxidizer mass flow. This paper describes analytical results of flow and structural properties for four different GOV models, using commercial software such as Fluent(Ver. 6.3.26) and NASTRAN(2005 r.2), PATRAN(2005 r.2). Analytical results show that GOVs could generate 2.3~3.8 kg/s of oxidizer mass flow rate and come up with 1.09~1.42 of safety factor.