• 대한기계학회논문집B
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• 제31권12호
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• pp.1002-1008
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• 2007

Natural convection flows in a doubly-inclined cubical air-filled cavity are numerically simulated by a solution code(PowerCFD) using unstructured cell-centered method. For a physical realizability, the cavity has one pair of opposing isothermal faces at different temperatures, $T_h\;and\;T_c$, respectively, the remaining four faces having a linear variation from $T_c\;to\;T_h$. The paper redefines a new doubly-inclined orientation for the cubical-cavity benchmark problem. Special attention is paid to three-dimensional thermal characteristics in natural convection according to the new orientation at $Ra=4\times10^4$. Comparisons of the average Nusselt number at the cold face are made with benchmark solutions and experimental results found in the literature. It is found that the average Nusselt number at the cold face has a maximum value at the doubly-inclined angle ranging from $40^{\circ}\;to\; 45^{\circ}$ We also report the effect of new orientation on the type of temperature structure in a doubly-inclined cubical-cavity.

• 한국연소학회지
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• 제12권1호
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• pp.11-20
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• 2007

The supersonic combustion experiments are carried out using T3 free-piston shock tunnel. Different shock tube fill pressures have various inflow conditions. $15^{\circ}$ inclined hydrogen fuel injection is located before the cavity. Oblique shock is generated from the cavity and reflects off the top and bottom wall. For non-reacting flow, fuel makes the shear layer thicker above the cavity therefore, the shock is generated just before the trailing edge. This research has self-ignition in the combustor. For reacting flow, as the equivalence ratio increases, flame starts to generate near the injector or occur in the recirculation zone before the injector. High fuel injection sustains the jet shape in the cross flow and air can mix with fuel along the shear layer. Therefore, two flame layers find above the cavity for high equivalence ratio.

• 한국가시화정보학회지
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• 제17권2호
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• pp.83-89
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• 2019

In this study, we show the maximum cavity radius prediction model that a droplet impacts an inclined bath. Surface tensions, viscosities, inclination angles of a bottom substrate, droplet diameters, falling heights of the droplet are varied for the experiment. We experimentally observe that the cavity grows in hemispherical shape like the cavity formed in a deep bath although the depth of the bath is non-uniform due to an inclined bottom substrate. We derive two theoretical models to predict the experimental results of the fully developed cavity. Although each model has error, we observe that qualitatively theoretical model predicts the trend of experiment results well.

• 한국연소학회지
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• 제12권1호
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• pp.21-27
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• 2007

The supersonic combustion experiments are carried out using T3 free-piston shock tunnel. Different shock tube fill pressures have various inflow conditions. $15^{\circ}$ inclined hydrogen fuel injection is located before the cavity. Oblique shock is generated at the trailing edge of the cavity and reflects off the top and bottom wall. For non-reacting flow, static pressures in low equivalence ratio are similar to those in no fuel injection. As equivalence ratio is increased, static pressures are increased in the duct. In the similar equivalence ratio, static pressures are increased when total enthalpy is decreased. For reacting flow, the flame is occurred near the cavity. The combustion is weak locally in the middle of the duct. The up and down pressure distribution in the duct means that the supersonic combustion is generated.

• 동력기계공학회지
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• 제6권1호
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• pp.36-42
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• 2002

Two-dimensional natural convection in an inclined open cavity with bottom heated, two side insulated and the top open was investigated using PIV(Particle-Image-Velocimetry) measurement. Experimental results are presented for Prandtl number, Pr=6.62, cavity aspect ratio, A=1.0, Rayleigh number from $1.294{\times}10^6\;to\;3.8841{\times}10 ^6$, and inclination angles, ${\alpha}=0$, 30 and 60 deg to the horizontal. It was found that the fluid rises along both side walls in the boundary layer region at ${\alpha}=0\;deg$, and the inclination of the cavity induced flow entrainment. The experimental results are in good agreement with the numerical results.

• 대한기계학회논문집
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• 제7권3호
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• pp.294-300
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• 1983

The purpose of this study is to investigate the radiant emission characteristics of diffuse equi-lateral trapezoid groove cavity for the case of uniform surface temperature. The theoretically developed results for the apparent emissivity are presented and the values of apparent emissivity for the trapezoid groove cavity were compared with those of the V-groove cavity. In the experimental part of this study, the test models were manufactured from 100x 100x 15mm copper plates on which the equi-lateral trapezoid cavities were grooved. The inclined angles of the groove were 30,45 and 60 degrees and the ratio of groove depth to base surface width varied from 1 to 5 for each inclined angle. As a result of this work, it was found that the trapezoid groove cavity was more general form of V-groove and the apparent emissivity of trapezoid groove cavity was greater than that of V-groove cavity. The resulting equation for the apparent emissivity in the trapezoid groove cavity was valid for the angles greater than 40 degrees.

• Ocean Systems Engineering
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• 제10권1호
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• pp.49-65
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• 2020

In this study, the effects of inclined shaft angle on the hydro-acoustic performance of cavitating marine propellers are investigated by a numerical method developed before and Brown's empirical formula. The cavitating blades are represented by source and vortex elements. The cavity characteristics of the blades such as cavitation form, cavity volume, cavity length etc., are computed at a given cavitation number and at a set advance coefficient. A lifting surface method is applied for these calculations. The numerical lifting surface method is validated with experimental results of DTMB 4119 model benchmark propeller. After calculation of hydrodynamic characteristics of the cavitating propeller, noise spectrum and overall sound pressure level (OASPL) are computed by Brown's equation. This empirical equation is also validated with another numerical results found in the literature. The effects of inclined shaft angle on thrust coefficient, torque coefficient, efficiency and OASPL values are examined by a parametric study. By modifying the inclination angles of propeller, the thrust, torque, efficiency and OASPL are computed and compared with each other. The influence of the inclined shaft angle on cavity patterns on the blades are also discussed.

• Wind and Structures
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• 제39권1호
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• pp.31-45
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• 2024

This paper examines the flow characteristics around an inclined prism with a U-shaped cross-section ("U-profile") and investigates the connection between the flow and flow-induced vibrations. The study employs a combined approach that involves wind tunnel experiments and computational fluid dynamics (CFD) using an unsteady Reynolds-averaged Navier-Stokes (RANS) turbulence model. Distinct vortex formation patterns are observed in the flow field surrounding the stationary inclined profile. When the cavity of the profile faces away from the incoming flow, large vortices develop behind the profile. Conversely, when the cavity is oriented towards the oncoming flow, these vortices form within the cavity. Notably, due to the slow movement of these large vortices through the cavity, the frequency at which vortices are shed in the negative inclination case is lower compared to the positive inclination, where they form in the wake. Wind tunnel experiments reveal an intermittent transition between the two vortex formation patterns at zero inclination. Large vortices sporadically emerge both in the cavity and behind the profile. The simulation results demonstrate that when these large vortices occur at a frequency close to the structure's natural frequency, they induce prominent pitch vibrations. This phenomenon is also sought after and presented in coupled vibration experiments. Additionally, the simulations indicate that when the natural frequency of the structure is considerably lower than the vortex shedding frequency, this type of vibration can be observed.

• 한국연소학회:학술대회논문집
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• 한국연소학회 2006년도 제33회 KOSCO SYMPOSIUM 논문집
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• pp.209-219
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• 2006

The supersonic combustion experiments are carried out using T3 free-piston shock tunnel. Different shock tube fill pressures have various inflow conditions. $15^{\circ}$ inclined hydrogen fuel injection is located before the cavity. Oblique shock is generated at the trailing edge of the cavity and reflects off the top and bottom wall. For non-reacting flow, static pressures in low equivalence ratio are similar to those in no fuel injection. As equivalence ratio is increased, static pressures are increased in the duct. In the similar equivalence ratio, static pressures are increased when total enthalpy is decreased. For reacting flow, the flame is occurred near the cavity. The combustion is weak locally in the middle of the duct. The up and down pressure distribution in the duct means that the supersonic combustion is generated.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2007년도 제29회 추계학술대회논문집
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• pp.293-296
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• 2007

호주국립대학의 T3 자유충격파관을 이용하여, 마하수 3.7의 유입 유동에 대해 비분사유동, 공동이전 경사분사유동, 공동내부 평행분사유동, 공동내부 역분사유동에 대해 주파수를 확인하고, 공동 유동 특성을 살펴보았다. 비분사유동은 고조파 형태의 주파수가 나타나지 않았으나 10 kHz 부근에서 비교적 큰 압력 스펙트럼이 나타났다. 공동 이전 경사분사는 공동의 앞전에서 박리되는 전단층의 두께를 증가시켜 공동 뒷전에서 발생하는 유동의 진동 현상을 현저히 감소시켰다. 공동 내부 평행분사는 공동의 뒷전에 분사 유동이 직접 부딪히게 되고, 공동의 진동 현상을 오히려 증가시켰다.