• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.35 no.8
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• pp.714-719
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• 2007

In this paper, we report experimental investigations on measurement of adiabatic wall temperature on a flat 2-D plate of high-speed impinging jet made by circular-shape nozzle at steady state condition using infra-red camera. Experiments have been conducted for the Reynolds number of 187,000 according to the change of nozzle-to-plate distance. Dimensionless number, recovery factor, has been used to represent the measured adiabatic wall temperature. And we compared the result obtained by using infra-red camera with that obtained by using thermocouple.

• Journal of KSNVE
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• v.7 no.1
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• pp.71-79
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• 1997

The objective of this study is to investigate experimentally the effect of surface conditions of the plate on the impinging jet noise. The experimental results about the spectrum, the sound pressure level and the directivity are pressented and discussed in relation with the surface conditions. Regardless of the surface conditions, the pure tones of high level are generated at the same frequency band and the overall sound power level of impinging jets is much higher than that of the free jet. However, the velocity dependence of the sound pressure level and the directivity are different between smooth surfaces and rough surfaces. The dependence of sound pressure level on the jet velocity shows that the smooth surface generates quadrupole-type sound like free jets. However, the perforated or the rough surface radiates sound power exactly proportional to the sixth power of the jet velocity, indicating that the source is fixed dipole type. The directivities of 1/3 octave band sound pressure level for both the free and impinging jet show the peak directivity at 115$^\circ$ upstream, probably due to the refraction associated with velocity gradient.

• Proceedings of the KSME Conference
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• 2002.08a
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• pp.525-528
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• 2002

The objective of this study is to investigate characteristics of flow by the Rod shape and the choice of the turbulent intensity enhancement section. The Rod was setup vertically to the way of a nozzle exit flow and nozzle diameter is 17mm. Rod height is 5mm and its shapes are square, triangle, and circle. Characteristics of fluid such as velocity vector distribution, kinetic energy, turbulent intensity, and etc. were visualized, observed, and considered at 3 kinds of Re No. such as 2000, 3000, and 4000. The characteristics of flow field were investigated in each case of the distance rate from the nozzle exit to impinging plate(H/B=8, 10). The temperature of water is $20^{\circ}E$ and the measurement region divided by 3 sections(I, II, III). The nozzle diameter is 17mm. As the experimental result by PIV measurement, scale of the vector profile showed a tendency to an unbalance parabola distribution as increasing of the Re No. When the impinging plates such as square, triangle, and circle shape are installed respectively in front of the flow accelerated, rod shape of the highest velocity vector is circle shape and rod shape of the highest turbulent Intensity is square shape.

• Proceedings of the Korean Vacuum Society Conference
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• 1998.02a
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• pp.62-62
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• 1998

다이아몬드상 카본은 경도, 열전도 둥이 다이아몬드와 비슷하면서도 박막 성장이 쉬워 다른 재료의 표면보호용 코탱막으로 웅용되고 있다. 최근에 다이아몬드상 카본 박막의 이러한 특성은 전계방출 음극 소자가 이온 충돌, 온도 상승에 의해 마모되는 것을 방지 하는데도 용용되고 있다. 이러한 보호막 기능뿐만 다이아몬드상 카본 박막용 편평한 기 판에 성장시켜 평판 전계방출 음극으로 이용하는 것도 시도되고 었다. 본 연구에서는 이 온빔 스퍼트링 방법으로 다이아몬드상 카본 박막을 성장시켰다. 합성하기 전 챔버의 기 본 압력은 3.2 X 10-7 Torr이었다. 기판으로는 타이타니움 평판, n-타엽의 실리콘 평판, I ITO가 코탱된 유리 평판올 사용하였으며, 중착 전에 기판올 400 V, 15 mA의 알곤 이온 으로 1분간 스퍼트링하여 불순물 막을 제거하였다. 박막 합성시에는 챔버 압력이 3.5 x 1 10-4 To$\pi$가 될 때까지 알곤을 채우고 알곤빔 전류는 30 mA에 고정시키고 빔 에너지를 각각 750, 1000, 1250 eV로 바꾸면서 타켓올 스퍼트랭하였다. 질소를 다이아몬드상 카본 박막애 첨가하면 n-타업 불순물 주입 효과가 있게된다. 질소가 첨가된 박막을 만들기 위 해서는 별도의 이온 총올 사용하여 탄소 타켓 스퍼트령과 동시에 기판에 질소 이온을 입 사시켰다. 만들어진 시료로부터 3 X 10-7 To$\pi$ 진공에서 전류-전압 특성올 조사하였다. 양극으로는 면평한 금속판올 음극 위 150 11m 높이에 셜치하였다. 박막의 물성은 전자 현미경, 오제 전자분광 둥으로 조사하였다. 다이아몬드상 카본 박막을 다른 종류의 편명 한 기판에 합성 조건올 바꾸면서 성장시켜 박악의 특성파 기판이 전계방출에 미치는 영 향을 조사하였다. 합성된 다이아몬드상 카본필름의 전자방출 특성은 기판의 종류와 필름 의 구조 및 필름의 두께에 따라 크게 변화하였다. 이러한 전자방출 거동으로부터 전계 방출 메커니즘을 제시하고자 하였다. 또한, 다이아몬드상 카본 박막으로부터의 전계방출 은 전기장올 인가하는 방법에도 영향을 받는다. 따라서, 본 연구에서는 전기장올 순환 인 가하면서 전계방출 전후의 박막 특성 변화를 조사하여 전계방출 메커니즘올 연구하였다.

• Journal of the Computational Structural Engineering Institute of Korea
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• v.36 no.5
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• pp.331-338
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• 2023

Modern bulletproof armor must be light and have excellent penetration resistance to ensure the mobility and safety of soldiers and military vehicles. The ballistic performance of heterogeneous structures of laminated flat plates as bulletproof armor depends on the arrangement of constituent materials for the same weight. In this study, we analyze bulletproof performance according to the stacking sequence of laminated bulletproof armor composed of Kevlar, ultra-high molecular weight polyethylene, and ethylene-vinyl-acetate foam. A ballistic analysis was performed by colliding a 7.62 × 51 mm NATO cartridge's M80 bullet at a speed of 856 m/s with six lamination arrangements with constituent materials thicknesses of 5 mm and 6.5 mm. To evaluate the bulletproof performance, the residual speed and residual energy of the projectile that penetrated the heterogeneous laminated flat plates were measured. Simulation results confirmed that the laminated structure with a stacking sequence of Kevlar, ultra-high molecular weight polyethylene, and ethylene-vinyl-acetate foam had the best bulletproof performance for the same weight.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.50 no.12
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• pp.829-838
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• 2022

This study conducts Hypervelocity Impact(HVI) simulations considering space objects with various shapes and different impact angles. A commercial nonlinear structural dynamics analysis code, LS-DYNA, is used for the present simulation study. The Smoothed Particle Hydrodynamic(SPH) method is applied to represent the impact phenomena with hypervelocity. Mie-Grüneisen Equation of State and Johnson-Cook material model are used to consider nonlinear structural behaviors of metallic materials. The space objects with various shapes are modeled as a sphere, cube, cylinder, and cone, respectively. The space structure is modeled as a thin plate(200 mm×200 mm×2 mm). HVI simulations are conducted when space objects with various shapes with 4.119 km/s collide with the space structures, and the impact phenomena such as a debris cloud are analyzed considering the space objects with various shapes having the same mass at the different impact angles of 0°, 30° and 45° between the space object and space structure. Although space objects have the same kinetic energy, different debris clouds are generated due to different shapes. In addition, it is investigated that the size of the debris cloud is decreased by impact angles.

• Transactions of the Korean Society of Automotive Engineers
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• v.14 no.2
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• pp.100-106
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• 2006

The behavior of spray impinging on the inclined constant temperature flat plate was experimentally investigated. To clarify the wall effect of a high pressure DISI injector, a relative angle of the inclined wall to a spray axis was varied. Spray penetration along the wall was observed optically and it was compared with that of a Fan spray type and Swirl type spray. To evaluate various spray motion quantitatively, a spray path penetration which describe the development of a spray tip along the wall was newly introduced. To observe the structure of an impinging spray, it was visualized by a controlled stroboscope light and its visualized image was captured on an CCD camera. Using the digital image of impinging spray $H_x$ and $R_x$ was extracted to clarify the structure of impinging spray. The main parameter of the relative position of the wall was the inclined angle which was defined as the angle was varied from $0^{\circ}$ (vertical impingement) to $60^{\circ}$ at the same condition.

• Solar Energy
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• v.15 no.1
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• pp.53-71
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• 1995

Experiments have been conducted on a planar, free surface jet of water to investigate the effects of aspect ratios(AR=6.67, 15, 26.67), average nozzle velocity($V_0=3.3m/s{\sim}78m/s$) and nozzle-to-plate spacings($Z/W=6{\sim}40$) on the characteristics of heat transfer, when 3 rectangular waterjets impinging on a flat plate which has the uniform heat flux. the scondary peaks which produced by circular jets also produced by rectangular water jets. The position of the scondary peaks depends upon the aspect ratio of nozzle. The heat transfer coefficient was subjected to the influence of aspect ratio. The heat transfer correlations and best position of nozzles which produced maximum heat transfer coefficient at stagnation point are provided.

• Solar Energy
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• v.17 no.1
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• pp.47-58
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• 1997

The objective of this research was to investigate the enhancement of heat transfer by wire mesh in impinging air jet system at the potential core region. The first experiment was carried out without mesh between nozzle exit and flat plate and the second experiment was done with mesh between them. When mesh was installed in front of the plate, heat transfer has been Increased due to the acceleration between rectangular halls and divided small jet In case clearances are changed, heat transfer comes to maximum under the condition of C=1mm, irrespective of nozzle exit velocity and H/B. Also the average heat transfer enhancement rate of a flat plate with mesh has been increased about 44% at maximum under the condition of U=18m/s, H/B=2 and C=1mm, compared to the result of a flat plate without mesh.

• Transactions of the Korean Society of Mechanical Engineers
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• v.11 no.2
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• pp.214-221
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• 1987

The purpose of this study is augmentation of heat transfer without additional power in the case of rectangular air jet which impinges vertically on the heating surface. The experimental results are obtained heat transfer augmentation of a two-dimensional impinging jet using the surface roughness of transverse repeated-rib type. The integral average heat transfer coefficient of ribbed plate is about two times larger than that of flat plate. In order to supplement the information about the mechanism of heat transfer augmentation, the flow structure in the stagnation region is visually studied by using the smoke wire technique. The heat transfer augmentation is due to the effect of stretching of large scale vortex in the stagnation region.