• 한국안전학회지
• /
• 제24권4호
• /
• pp.17-21
• /
• 2009

The fire whirl occurring in the urban and/or wildland fire is generated by the instabilities of atmosphere. The fire whirl is a rare phenomenon, but highly destructive because it has high inhalation and lift force. In this study, experimental study is performed with oriental oak leaves, for investigating of the fire whirl characteristics occurred in wildland fire. As a result of experiment, the circulation intensity increases as increasing of the induced air velocity, and then the fire whirl occurs. Also, the heat release rate and flame height increase 22% and 18% in highest circulation.

• Journal of Ship and Ocean Technology
• /
• 제12권3호
• /
• pp.14-25
• /
• 2008

Recently, there has been a serious effort to design a wing in ground effect (WIG) craft. Vehicles of this type might use low aspect ratio wings defined as those with smaller than 3. Design and prediction techniques for fixed wings of relatively large aspect ratio are reasonably well developed. However, Aerodynamic problems related to vortex lift on wings of low aspect ratio have made it difficult to use existing techniques. In this work, we firstly focus on understanding aerodynamic characteristics of low aspect ratio wings and comparing the results from experimental measurements and currently available numerical predictions for both inviscid and viscous flows. Second, we apply an improved numerical method, "B-spline based high panel method with wake roll-up modeling", to the same problem.

• 비파괴검사학회지
• /
• 제36권4호
• /
• pp.288-294
• /
• 2016

Flexible ECT (eddy current array) probe를 사용하여 판재 및 용접부에 존재하는 notch 결함을 MS-5800E와 OmniScan MX 장비로 검출능력을 비교하고, 주파수와 lift-off를 변수로 신호의 특성을 비교하고자 하였다. 실험 결과, 500, 1000, 1500 kHz를 사용하였을 때 notch 깊이가 증가할수록 신호의 진폭이 증가하는 것으로 나타났고, lift-off 변화에 따른 신호의 진폭은 선형적으로 감소하였다. 또한 용접부 결함은 probe와 시험체의 접촉면에 밀접한 관계가 있다. Probe와 시험체의 접촉면이 양호한 경우 검출감도가 우수하고 그렇지 않은 경우에는 검출감도가 떨어지는 것을 알 수 있었다.

• 한국연소학회:학술대회논문집
• /
• 한국연소학회 2007년도 제34회 KOSCO SYMPOSIUM 논문집
• /
• pp.13-18
• /
• 2007

When triple flames propagated in a diverging channel, the effects of fuel dilution on the lift-off characteristics of triple flames were investigated. A multi-slot burner was used to stabilize the lift-off flame especially at weak fuel concentration gradients. It was reported that there is a maximum propagation velocity at a critical concentration gradient in an open jet regardless of fuel dilution. The enhancement of a diffusion flame affected to increase the propagation velocity around critical concentration gradients. However, the influence of a confined channel on the structure of triple flames according to fuel dilution needs to be investigated compared with an open jet case. This study aimed to examine the effect of a confined channel on the structure and the propagation velocity of the triple flames according to fuel dilution. Lift-off height and propagation velocity of triple flames were investigated by employing three kinds of fuel compositions diluted by nitrogen (0%, 25%, 50% $N_2$), Fuel dilution reduced the propagation velocity of triple flame in a confined channel mainly due to the decrease of flame temperature in premixed branch. Despite the difference in fuel dilution, the propagation velocity has a maximum value at a specific fuel concentration gradient even though the critical concentration gradient increases with fuel dilution. And the critical concentration gradient in a confined channel is larger than that in an open jet due to enhancement of convective diffusion.

• 한국연소학회지
• /
• 제17권1호
• /
• pp.48-57
• /
• 2012

Laminar lifted propane coflow-jet flames diluted with nitrogen were experimentally investigated to determine heat-loss-related self-excitation regimes in the flame stability map and elucidate the individual flame characteristics. There exists a critical lift-off height over which flame-stabilizing effect becomes minor, thereby causing a normal heat-loss-induced self-excitation with O(0.01 Hz). Air-coflowing can suppress the normal heat-loss-induced self-excitation through increase of a Peclet number; meanwhile it can enhance the normal heat-lossinduced self-excitation through reducing fuel concentration gradient and thereby decreasing the reaction rate of trailing diffusion flame. Below the critical lift-off height. the effect of flame stabilization is superior, leading to a coflow-modulated heat-loss-induced self-excitation with O(0.001 Hz). Over the critical lift-off height, the effect of reducing fuel concentration gradient is pronounced, so that the normal heat-loss-induced self-excitation is restored. A newly found prompt self-excitation, observed prior to a heat-loss-induced flame blowout, is discussed. Heat-loss-related self-excitations, obtained laminar lifted propane coflow-jet flames diluted with nitrogen, were characterized by the functional dependency of Strouhal number on related parameters. The critical lift-off height was also reasonably characterized by Peclet number and fuel mole fraction.

• 대한기계학회논문집B
• /
• 제34권7호
• /
• pp.665-670
• /
• 2010

등방성 난류에서 부유된 무거운 입자의 운동에서, 입자의 회전이 고려되었을 때 입자의 분산 특성에 나타난 변화를 살펴보았다. 입자의 회전을 고려함으로 인해 추가로 고려되는 양력은 그 크기가 작은 것으로 알려져 있고, 따라서 많은 연구에서 회전에 의한 효과는 무시되었다. 본 연구에서는 라그랑지안 기법으로 추적한 입자의 궤적에 미치는 양력의 크기를 속도와 가속도의 자기상관함수 및 확률밀도함수를 통해 정량적으로 살펴보았다. 속도 통계량에서는 양력에 의한 효과가 무시할 만 했으나, 가속도와 관련된 통계는 양력에 의한 영향이 있는 것으로 확인되었다. 난류의 가속도는 간헐성을 띄며, 간헐적인 특성은 난류 구조와 관련이 있다는 것이 알려져 있다. 따라서 입자에 작용하는 양력과 난류구조에 연관성이 있다는 유추가 가능하다.

• 한국가스학회지
• /
• 제19권4호
• /
• pp.35-40
• /
• 2015

열교환기의 전열관군은 전열관군 외부로 흐르는 유동에 의해 유동 유발 진동이 일어나며 이것으로 말미암아 전열관군에서 파손을 야기할 수 있어서 열교환기의 구조적 안정성을 위해 열교환기의 전열관군에서 유동 유발 진동 특성을 규명할 필요가 있다. 일반적인 열교환기 전열관군에서 유동 유발 진동에 관한 실험적 연구는 기존에 많이 진행되어 오고 있으며 유동 유발 진동에 대한 무차원 PSD(Power Spectral Density) 함수를 무차원 주파수인 Strouhal 수, fU/U의 함수로 도출된 실험적 결과들이 도출되어 있다. 본 연구는 열교환기 단일 원관에서 유동 유발 진동에 관한 기존의 연구들의 결과를 전산유체해석을 통해 검증하고 배열회수 보일러의 전열관군의 유동 유발 진동 특성에 적용하기 위한 기반을 마련하는 것을 목적으로 한다. 이러한 것을 위해 단일 원관에서 비정상 상태 유동해석을 수행하여 주기적인 와동 발생 특성과 원관에서의 양력과 항력의 변화 특성을 살펴보았다. 또한 원관에서 양력과 항력의 변동 특성으로부터 유동 유발 진동에 따른 PSD 특성 결과를 도출하여 기존의 연구들과 비교를 통해 원관 주위의 PSD 특성을 살펴보았으며 양력과 항력의 진폭과 주파수의 특성을 규명하였다.

• 한국정밀공학회:학술대회논문집
• /
• 한국정밀공학회 2007년도 춘계학술대회 논문집
• /
• pp.591-592
• /
• 2007

• Journal of Mechanical Science and Technology
• /
• 제17권5호
• /
• pp.776-783
• /
• 2003

A low speed wind tunnel test was conducted for full-scale model of an unmanned aerial vehicle (UAV) in Korea Aerospace Research Institute (KARI) Low Speed Wind Tunnel(LSWT). The purpose of the presented paper is to illustrate the general aerodynamic and performance characteristics of the UAV that was designed and fabricated in KARI. Since the testing conditions were represented minor portions of the load-range of the external balance system, the repeatability tests were performed at various model configurations to confirm the reliability of measurements. Variations of drag-polar by adding model components such as tails, landing gear and test boom are shown, and longitudinal and lateral aerodynamic characteristics after changing control surfaces such as aileron, flap, elevator and rudder are also presented. To explore aerodynamic characteristics of an UAV with model components build-up and control surface deflections, lift curve slope, pitching moment variation with lift coefficients and drag-polar are examined. The discussed results might be useful to understand the general aerodynamic characteristics and drag pattern for the given UAV configuration.

• International Journal of Aeronautical and Space Sciences
• /
• 제16권1호
• /
• pp.8-18
• /
• 2015

A numerical simulation for a nonslender BWB UCAV configuration with a rounded leading edge and span of 1.0 m was performed to analyze its aerodynamic characteristics. Numerical results were compared with experimental data obtained at a free stream velocity of 50 m/s and at angles of attack from -4 to $26^{\circ}$. The Reynolds number, based on the mean chord length, is $1.25{\times}106$. 3D multi-block hexahedral grids are used to guarantee good grid quality and to efficiently resolve the boundary layer. Menter's shear stress transport model and two transition models (${\gamma}-Re_{\theta}$ model and ${\gamma}$ model) were used to assess the effect of the laminar/turbulent transition on the flow characteristics. Aerodynamic coefficients, such as drag, lift, and the pitching moment, were compared with experimental data. Drag and lift coefficients of the UCAV were predicted well while the pitching moment coefficient was underpredicted at high angles of attack and influenced strongly by the selected turbulent models. After assessing the pressure distribution, skin friction lines and velocity field around UCAV configuration, it was found that the transition effect should be considered in the prediction of aerodynamic characteristics of vortical flow fields.