• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.3
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• pp.1-9
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• 2005

The interaction between hypersonic free stream and side jet flow at high altitudes is investigated by using the direct simulation Monte Carlo (DSMC) method. In order to alleviate the difficulty associated with the large density difference between the free stream and the side jet flow and to simulate the two flows simultaneously, a weighting factor technique is applied. For validation, the corner flow over a pair of plates perpendicularly attached is calculated with and without a side jet, and the results are compared with experiment. For a more realistic configuration, the flow past a blunted cone cylinder shape is solved. The leeward or windward jet is injected into the free stream and the effect on the aerodynamic force and moment is observed at various flow angles. The lambda shock effect and the wake structure are studied in terms of the surface pressure differential. A higher interaction between the free stream and the side jet flow is observed when the side jet is injected in the windward direction.

• Transactions of the Korean Society of Mechanical Engineers
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• v.15 no.1
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• pp.355-365
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• 1991

New definition for the interaction of flames is introduced and interacting turbulent diffusion flames issuing from two rectangular nozzles are investigated on the basis of the definition. Theoretical study through numerical model is carried out and experiment for validation is conducted. The characteristics of interaction due to the variation of major parameters such as nozzle spacing, Reynolds number and nozzle aspect ratio are studied. Results show that strong interaction occurs for small nozzle spacing, small Reynolds number and large aspect ratio. In order of their magnitude, the intensity of interactions on the individual transport mechanism is momentum, heat and mass. It is also found that interaction makes flames longer, tilted and finally merged. Increase of velocities and temperature, decrease of oxygen concentration and depression of turbulence are occurred in the region between flames.

• Journal of Korean Society of Coastal and Ocean Engineers
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• v.20 no.5
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• pp.491-497
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• 2008

The effect of wave and current interactions on jet-like current flowing against waves was investigated based on numerical simulations. The numerical simulations were conducted using a model system of REF/DIF(a wave model) and SHORECIRC(a current model). In the simulations, irregular waves refracted due to the jet-like opposing current were focused along the centerline of current, and the jet-like current was spreaded earlier when the wave heights become larger. The numerical results show that the rapid change of wave height distribution in transverse direction near current inlet plays a significant role to spread the jet-like current. In other words, the radiation stress gradients acting in transverse direction have a more significant effect on the jet-like current than its gradients acting in flowing direction which tend to accelerate the current do. In conclusion, it is indispensible to take into account the interaction between waves and current when the jet-like current such as river mouth meets opposing waves.

• Proceedings of the Korean Vacuum Society Conference
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• 2013.02a
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• pp.514-514
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• 2013

플라즈마와 혈액의 상호작용 특성을 파악하기 위해 혈액응고 실험을 하였다. 생체에 적용 가능한 바이오 플라즈마 소스를 개발하여 다양한 조건으로 혈액에 플라즈마를 조사하였다. 혈액 응고의 정량적인 측정 방법으로 혈액의 저항을 측정하였다. 본 실험에 사용된 플라즈마 제트 장치는 의료용 바늘과 유리관, 외부 접지로 이루어져 있다. 플라즈마 제트 장치는 고전압 전극이 유리관 안에 위치하고 접지 전극이 유리관 바깥에 위치한다. 의료용 바늘을 통해 Ar gas를 주입하며, 약 2 kV의 전압을 인가하여 방전시켰다. 자연적으로 혈액을 응고시킨 경우, 칼슘 클로라이드를 첨가하여 응고시킨 경우, Ar gas 및 온풍을 단독적으로 불어넣은 경우, 그리고 플라즈마 제트를 조사한 경우로 나누어 실험을 진행하였다. 두개의 떨어진 전극 사이에 일정량의 혈액을 배치시켜 저항을 측정하여 응고 정도를 파악하였다. 플라즈마 제트를 조사하였을 경우 아무것도 처리하지 않은 자연상태의 혈액보다 혈액이 응고되는 속도가 빠르게 나타났다. Ar gas와 온풍을 단독으로 불어넣어 준 경우와 혈액 표면이 응고되었으나, 약 20초가 지나면 다시 원래 상태의 혈액으로 돌아감을 확인하였다. 플라즈마 제트를 혈액에 조사했을 때는 혈액이 이전의 혈액 상태로 돌아가는 경향이 나타나지 않았다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2002.04a
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• pp.60-60
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• 2002

비행탄의 종말속도증대를 위하여 고체램제트를 이용하는 개념은 현재 세계적으로 여러나라에서 연구 중에 있다. Solid Fuel Ramjet Propulsion(고체연료 렘제트 추진)은 로켓추진에 비하여 월등히 높은 비추력을 가지며 구조적으로 매우 간단하여 탄의 사거리 및 평균속도를 증대시키는 좋은 수단으로 사용되고 있다. 그러나 간단한 구조에도 불구하고 고체렘제트의 작동은 매우 다양한 물리적 현상이 연관되므로 필요한 성능을 얻기 위해서는 이들의 상호 작용을 고려하여 설계의 최적화 및 성능 예측이 필요하다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1998.10a
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• pp.14-14
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• 1998

램제트 엔진은 초음속에서 공기가 충격파를 통해 아음속으로 속도가 낮아지고 압력이 증가하는 램 압축 현상을 이용하되 압축기를 사용하지 않고 아음속 상태에서 연소하는 구조로 되어 있다. 따라서 각 부품의 성능은 독립적이지 않으며 전체적인 성능을 규명하기 위해서는 공기 흡입구와 연소실, 연료 분사체계 등의 상호작용을 고려하여 유동의 특성과 그에 따른 연소현상의 특성을 함께 고려해야만 한다. 본 연구에서는 속도 범위 Mach 5이내, 고도 30km이내의 운항조건을 갖는 유도 무기에 장착될 램제트 엔진 개발을 위한 연구의 첫 번째 단계로써, 램제트 연소실내의 유동장해석을 실험과 수치해석 두 분야로 나누어 수행하였다.

• Journal of the Korea Society for Simulation
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• v.31 no.3
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• pp.11-21
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• 2022

Two methods for analyzing interaction between shaped charge jets and targets are taken in AVEAM-MT (ADD Vulnerability and Effectiveness Assessment Model for Materiel Target), which is a model for vulnerability analysis of materiel targets and being developed by ADD. One is an empirical method improved from the Fireman-Pugh technique for rapid penetration calculation into target components. The other is ADD-TSC(ADD Tandem Shaped Charge), which is a physics-based model extended to be applicable for shaped charge jets from the Walker-Anderson penetration model for higher fidelity analysis. In this paper, the two methods are briefly described, and the empirical technique is compared to the physics-based model in the prediction of residual penetration capacity. The latter is also compared to experimental results found in literature in predicting penetration capacity. These comparisons show that both methods can be used for fast calculations or higher fidelity calculations in vulnerability analysis models like AVEAM-MT which is required to perform a considerable amount of iterative simulation for damage analysis.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.32 no.8
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• pp.64-71
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• 2004

A computational study on the supersonic flow around the lateral jet controlled missile has been performed. For this purpose a three dimensional Navier-Stokes computer code(AADL3D) has been developed and case studies have been performed by comparing the normal force coefficient and the moment coefficient of a missile body for different jet flow conditions including jet pressure and jet Mach number. The results show different behavior of normal force and moment variation according to jet pressure variation and jet Mach number variation. From the detailed flow field analyses, it is verified that most of the normal force loss and the pitching moment generation are taken place at the low-pressure region behind the jet nozzle. Furthermore, it is shown that the pitching moment can be efficiently reduced by obtaining the lateral thrust through higher jet Mach number rather than through high jet pressure.

• Journal of the Korean Vacuum Society
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• v.21 no.6
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• pp.312-321
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• 2012

The electric potential of plasma column is measured with the high voltage probe in a pair of atmospheric plasma jets operated by AC-voltage. According to the polarity of voltage applied to the electrodes, the polarity of plasma column potential has the same polarity of applied voltage. The high potential of plasma column at the side of high voltage electrode is decreased linearly along the plasma column to the ground side. Therefore, the plasma column seams to be a kind of resistor whose resistivity is a few 10s $M{\Omega}/m$. In the experiment of double-jets system, the polarity of plasma potential is verified to be the same polarity to the applied voltage. When the different voltage polarities are applied to the electrodes of double plasma jets, the attractive force is acted between two plumes at the merged plasma and the plasma potential is measured to be low as a few 10s V. When the same polarity of voltage is applied to the electrode, the repulsive force is acted and the plasma potential is measured to be high as a several 100s V at the merged plumes. In the exposure of plasma plume on the bio-substrate with the double plasma jets, the electric shock and thermal damage might be proportional to the plasma power which is the multiplication of the plasma potential and the plasma current.

• Journal of the Korean Society of Propulsion Engineers
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• v.5 no.1
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• pp.26-33
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• 2001

Thrust vector control system is control device which is mounted exit of the nozzle to generate pitch, yaw and roll directional force by deflecting flow direction of the supersonic jet from the nozzle. By obtaining control force, jetvane which is exposed in jet flow is working thermal and aerodynamic load. Axial thrust loss and side thrust is affected by shock patterns and interactions between jetvanes according to jetvane geometry and turning angle. In this study, we designed 6 types of jetvane to evaluate pitch, yaw and roll characteristics of ietvane in supersonic flow, and perform the cold flow test in range of turning angles of jetvanes between $0^{\cire}$ and $25^{\cire}$ by $5^{\cire}$ respectively. Also, calculation is going side by side to analyse flow interaction. Results show that there is no interactions between jetvanes upto turning angle 20$^{\circ}$, chord and lead length ratio is very important parameter to aerodynamic performance and maximum thrust loss is appeard to 17% of axial thrust in roll directional control.