• Water for future
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• v.27 no.3
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• pp.35-43
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• 1994

Because a failure to provide enough plunge pool depth can create a risk to the structural stability of the psillways or dams, many researchers have proposed experimental formulas for claculating ultimate scour depth under jet issued from spillways and pipe culverts. For the design purposes of a plunge pool, scour potential distribution is important as much as the ultimate scour depth is. In this study scour potential distributions near the jet impinging point on a porous plane which can simulate a real cohesionless movable flat bed has been measured. Experimental results showed that scour potential distributions are geometrically similar to each other provided the angle of jet impact was the same. Statistical analysis of experimental results showed that scour potential distributions for the design purposes of a plunge pool could be expressed by a single equation within a range of this experiment. The proposed formula for the prediction of scour potential distributions agrees well with experimental measurements.

• Journal of Mechanical Science and Technology
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• v.14 no.1
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• pp.113-120
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• 2000

This study has developed a new liquid crystal calibration technique using Neural networks with median filtering and applied this technique to heat transfer measurements. To verify the validity of this new measurement technique, the local Nusselt numbers on a flat plate surface subjected to an axisymmetric impinging jet were measured and compared with the results by the conventional Hue-temperature calibration technique under the same conditions. Because the Neural networks predict the non-linear relations between temperatures and corresponding R, G, B values, Neural networks-median filtering calibration technique can utilize a much wider color band in the experiment than the Hue-temperature calibration technique, resulting in a significant reduction in the experimental time.

• Journal of the Korean Society of Propulsion Engineers
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• v.3 no.2
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• pp.66-74
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• 1999

In this study, the heat transfer augmentation without additional blower power was obtained by using punched plate. Though this scheme has some disadvantages such as decrease of momentum caused by the punched plate, it has significantly increased heat transfer coefficients in the stagnation region. Compared with the case of no punched plate, heat transfer coefficients were increased by punched plate more than 2 times near the optimum condition determined in this study. Liquid crystal and hue-capturing technique were used in this study to obtain heat transfer coefficients.

• Journal of computational fluids engineering
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• v.8 no.2
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• pp.1-7
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• 2003

The V2F turbulence model, which has shown very good performance in several test cases at low speeds, has been applied to supersonic ramp flow with 20. corner angle at the free stream Mach number of 2.79. The flow is known to manifest strong shock wave/turbulent boundary layer interactions. As a comparative study, low-Reynolds k-ε models are also considered. While the V2F model predicts wall-pressure distribution well, it relatively predicts larger separation bubble and higher skin-friction after the reattachment than the experimental data. Although the ellpticity of f equation is the characteristics of incompressible flows, the converged solutions are acquired in the compressible flow with shock waves. The effect of the realizability constraints used in the model is also examined. In contrast to the result of impinging jet flows, the realizability bounds proposed by Durbin deterioate the overall solutions of the supersonic ramp flow.

• Journal of computational fluids engineering
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• v.16 no.1
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• pp.36-41
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• 2011

Numerical simulation of air-launched rockets from a helicopter was conducted to investigate the aerodynamic interference between air-launched rocket and helicopter. For this purpose, a three-dimensional inviscid flow solver has been developed based on unstructured meshes. An overset mesh technique was used to describe the relative motion between rocket and rocket launcher. The flow solver was coupled with six degree-of-freedom equation to predict the trajectory of free-flight rockets. For the validation, calculations were made for the impinging jet with inclined plate. The rotor downwash of helicopter was calculated and applied to simulation of air-launched rocket. It is shown that the rotor downwash has non-negligible effect on the air-launched rocket and its plume development.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.26 no.10
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• pp.1465-1471
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• 2002

This paper deals with the development of a new method that can obtain the heat transfer coefficient and the reference free stream temperature simultaneously. The method is experimentally verified through comparison with results in convective heat transfer experiments of a circular impinging jet using two narrow-band TLCs. The general method described in this paper is highly recommended to many heat transfer models with the unknown or ambiguous free stream temperature.

• Journal of the Korean Society of Combustion
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• v.8 no.1
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• pp.36-45
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• 2003

The subject of turbulent premixed flames has been focused by many researchers for a number of decades. Especially, Borghi suggested a magnificent diagram classifying turbulent combustion areas and Lipatnikov and Chomiak modified this diagram. Recently, experimental techniques have been developed so that we can use PIV for measuring 2D velocity field and apply OH PLIF techniques for obtaining flame locations. In present study, a new diagram is proposed using strain rates and OH signal intensity. Thus, simultaneous PIV and OH PLIF measurements are used for shear strain rates and flame locations, respectively. It is believed that the shear strain rates represent flow characteristics such as turbulence intensity and the OH intensity indicates the flame characteristics such as burning velocities.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1998.10a
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• pp.28-28
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• 1998

단일 충돌제트의 경우 충돌면에서의 열전달 효과는 제트 출구와 충돌면 사이의 간격, 노즐 형상에 따른 제트출구의 초기조건, Re$_{D}$수 변화와 충돌면의 형상이나 표면거칠기 등에 따라 변화하게 된다. 그러나 수직 충돌제트의 경우 정체영역에서의 국소적인 열전달 향상은 용이하나 반경 방향으로 열전달이 점차 감소하게 된다. 따라서 충돌면의 전반적인 열전달 향상을 위해서는 열전달이 정체점보다 상대적으로 낮은 영역에서 열전달 향상이 필요하다. 또한, 실제 적용시 충돌면의 형상이나 협소한 공간에서 노즐위치의 제약으로 인하여 충돌제트가 수직으로 분사되는 경우보다 경사진 제트가 더욱 많이 응용된다. 더욱이, 수직충돌제트가 사용되는 많은 상황에서도 주위의 다른 공기 흐름의 영향으로 인하여 실제 제트가 경사각을 갖고 분사되어진다 이러한 경사충돌제트의 중요성에도 불구하고 경사충돌제트에 대한 연구는 수직충돌제트에 대한 연구보다 상대적으로 적게 이루어져 왔다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1998.10a
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• pp.27-27
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• 1998

제트에 있어서 유동특성은 제트초기의 생성되는 불안정성이 하류에서의 와류성장에 영향을 끼치게 되기 때문에 중요하게 되며, 와류의 조절을 통해 충돌면에의 열전달 효과의 변화를 가져올 수 있게 된다 따라서 본 연구에서는 FFT를 이용하여 제트의 와류생성과 병합의 주파수 특성을 연구하고, 이에 적절한 주파수로 와류를 여기 하여 자유제트의 유동특성 변화와 이에 따른 충돌 면에서의 충돌제트의 유동 및 열전달 특성을 고찰하였다. 제트의 음향을 통한 여기를 함으로써 생성되는 와류형성 및 병합 특성 변화는 연기열선법(smoke-wire method)과 속도 및 난류강도 특성 결과를 통해 확인 할 수 있었는데, 이는 자연적으로 생성되는 와류의 주파수(고유 주파수)와 관련하여 고유주파수의 조화성분 또는 부조화성분의 주파수를 가함으로써 와류의 병합을 촉진시키거나 억제하는 효과를 나타내기 때문이다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2003.05a
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• pp.27-31
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• 2003

An experimental investigation for impingement of under-expanded, axisymmetric jets on a flat plate has been conducted, and the surface pressure, the adiabatic wall temperature distributions on the plate have been measured in detail at small nozzle-to-plate distances. the pressure ratio and the nozzle-to-plate distance have been considered as experimental parameters.