• International Journal of Aeronautical and Space Sciences
• /
• 제7권1호
• /
• pp.13-26
• /
• 2006

When the stagnation temperature of a perfect gas increases, the specific heat for constant pressure and ratio of the specefic heats do not remain constant any more and start to vary with this temperature. The gas remains perfect: its state equation remains always valid, with exception that it will be named by calorically imperfect gas. The aim of this research is to develop the relations of the necessary thermodynamics and geometrical ratios. and to study the supersonic flow at high temperature. lower than the threshold of dissociation. The results are found by the resolution of nonlinear algebraic equations and integration of complex analytical functions where the exact calculation is impossible. The dichotomy method is used to solve the nonlinear equation. and the Simpson algorithm for the numerical integration of the found integrals. A condensation of the nodes is used. Since. the functions to be integrated have a high gradient at the extremity of the interval of integration. The comparison is made with the calorifcally perfect gas to determine the error made by this last. The application is made for the air in a supersonic nozzle.

• 한국해양공학회지
• /
• 제27권2호
• /
• pp.39-46
• /
• 2013

In this study, the impact loads on tank walls by sloshing phenomena and on a tall structure in a three-dimensional rectangular tank were predicted using multiphase flow simulations. The solver was based on the CIP/CCUP (Constraint interpolation CIP/CIP combined unified procedure) method, and the THINC-WLIC (Tangent hyperbola for interface capturing-weighted line interface calculation) scheme was used to capture the air-water interface. For the convection terms of the Navier-Stokes equations, the USCIP (Unsplit semi-lagrangian CIP) method was adopted. The results of simulations were compared with those of experiments. Overall, the comparisons were reasonably good.

• 한국추진공학회:학술대회논문집
• /
• 한국추진공학회 2004년도 제22회 춘계학술대회논문집
• /
• pp.186-191
• /
• 2004

The reactive flowfield of the transverse injecting combustor has been studied using Euler-Lagrange method in order to develop an efficient solution procedure for the understanding of liquid spray combustion in the transverse injecting combustor which has been widely used in ramjets and turbojet afterburners. The unsteady two-dimensional gas-phase equations have been represented in Eulerian coordinates and the liquid-phase equations have been formulated in Lagrangian coordinates. The gas-phase equations based on the conservation of mass, momentum, and energy have been supplemented by combustion. The vaporization model takes into account the transient effects associated with the droplet heating and the liquid-phase internal circulation. The droplet trajectories have been determined by the integration of the Lagrangian equation in the flow field obtained from the separate calculation without considering the iterative effect between liquid and gas phases. The reported droplet trajectories had been found to deviate from the initial conical path toward the flow direction in the very end of its lifetime when the droplet size had become small due to evaporation. The integration scheme has been based on the TEACH algorithm for gas-phase equation, the second order Runge-Kutta method for liquid-phase equations and the linear interpolation between the two coordinate systems. The calculation results has shown that the characteristics of the droplet penetration and recirculation have been strongly influenced by the interaction between gas and liquid phases in such a way that most of the vaporization process has been confined to the wake region of the injector, thereby improving the flame stabilization properties of the flowfield.

• 대한기계학회논문집B
• /
• 제22권6호
• /
• pp.725-733
• /
• 1998

The pressure fluctuation on the surface of a submerged body has been recognized as a dominant noise source. There have been many studies concerning the flow induced noise on a flat plate. However, the noise over an axisymmetric body has not been well reported. This paper addresses the way in which we have investigated the mechanism of noise generation due to an axisymmetric body. The associated experiments and signal processing methods are introduced. A 3-dimensional axisymmetric body whose length and diameter were 2 m and 10.4 cm, was prepared as a test specimen. The wall pressure on the surface of the body was measured in a large scale low noise wind tunnel at KIMM(Korea Institute of Machinery and Metals). To measure the wall pressure, we used two microphone arrays which were tangential and normal to the flow. Based on the measured signal, frequency-wavenumber spectrum which explains the structure of turbulence noise, was estimated. Tangential to the flow, there exists convective ridge at a relatively higher wavenumber region; this can cause spatial aliasing. To circumvent this problem, the cross spectrum was interpolated. The interpolation has been performed by unwrapping the phase and smoothing the cross spectrum. The phase unwrapping was done based on the Corcos model; the phase of cross spectrum decreases linearly with the distance between microphones. Aforementioned signal processings are possible by employing the experimental results that the estimated wavenumber spectrum quite resembles the Corcos model. We try to modify the Corcos model which is applicable to the flat plate, by altering the magnitude of cross spectrum to fit the experimental data more accurately. We proposed that this wavenumber spectrum model is suitable for the 3-dimensional axisymmetric body. Normal to the flow, there exists a little correlation between signals of different microphones. The circumferential wavenumber spectrum contains uniform power along the wavenumbers.

• Journal of Mechanical Science and Technology
• /
• 제20권12호
• /
• pp.2218-2229
• /
• 2006

A conservative finite-volume numerical method for unstructured grids with the cell-centered method has been developed for computing flow and heat transfer by combining the attractive features of the existing pressure-based procedures with the advances made in unstructured grid techniques. This method uses an integral form of governing equations for arbitrary convex polyhedra. Care is taken in the discretization and solution procedure to avoid formulations that are cell-shape-specific. A collocated variable arrangement formulation is developed, i.e. all dependent variables such as pressure and velocity are stored at cell centers. For both convective and diffusive fluxes the forms superior to both accuracy and stability are particularly adopted and formulated through a systematic study on the existing approximation ones. Gradients required for the evaluation of diffusion fluxes and for second-order-accurate convective operators are computed by using a linear reconstruction based on the divergence theorem. Momentum interpolation is used to prevent the pressure checkerboarding and a segregated solution strategy is adopted to minimize the storage requirements with the pressure-velocity coupling by the SIMPLE algorithm. An algebraic solver using iterative preconditioned conjugate gradient method is used for the solution of linearized equations. The flow analysis code (PowerCFD) developed by the present method is evaluated for its application to several 2-D structured-mesh benchmark problems using a variety of unstructured quadrilateral and triangular meshes. The present flow analysis code by using unstructured grids with the cell-centered method clearly demonstrate the same accuracy and robustness as that for a typical structured mesh.

• 한국전산유체공학회지
• /
• 제19권2호
• /
• pp.86-92
• /
• 2014

In this paper, prediction of separation trajectory for Two-stage-To-Orbit space launch vehicle has been numerically simulated by using an aerodynamic database based on steady state analysis. Aerodynamic database were obtained for matrix of longitudinal and vertical positions. The steady flow simulations around the launch vehicle have been made by using a 3-D RANS flow solver based on unstructured meshes. For this purpose, a vertex-centered finite-volume method was adopted to discretize inviscid and viscous fluxes. Roe's finite difference splitting was utilized to discretize the inviscid fluxes, and the viscous fluxes were computed based on central differencing. To validate this flow solver, calculations were made for the wind-tunnel experiment model of the LGBB TSTO vehicle configuration on steady state conditions. Aerodynamic database was constructed by using flow simulations based on test matrix from the wind-tunnel experiment. ANN(Artificial Neural Network) was applied to construct interpolation function among aerodynamic variables. Separation trajectory for TSTO launch vehicle was predicted from 6-DOF equation of motion based on the interpolated function. The result of present separation trajectory calculation was compared with the trajectory using experimental database. The predicted results for the separation trajectory shows fair agreement with reference[4] solution.

• Spatial Information Research
• /
• 제20권5호
• /
• pp.1-13
• /
• 2012

본 연구는 그동안 이산화탄소의 유동 방향 연구에서 지적된 지상관측자료의 시 공간적 제약성을 극복하고자, 최초의 온실가스 측정 전용 위성인 GOSAT을 활용하여 동북아시아 지역의 계절별 이산화탄소의 유동 방향을 평가하고자 하였다. 이를 위해 크리깅 분석을 적용하여 결측값을 보완하고, 이방성 베리오그램을 통해 전체적인 이산화탄소의 유동 방향을 결정하였다. 그 결과 동북아시아의 이산화탄소 공간적 분포 양상은 위도대에 일치하는 변화추세를 확인할 수 있었으며, 계절별 유동성은 봄, 가을, 겨울의 경우 남동쪽 및 동쪽으로 유동되는 이산화탄소가 주를 이루어 나타났으며, 여름에 경우 북쪽 및 북동쪽으로 이동하는 흐름이 나타났다. 이러한 결과는 동북아시아 지역에서 나타나는 계절풍과 유사한 흐름으로 주로 서에서 동으로 이동되는 경우가 주를 이루고 있음을 알 수 있으며, 이는 중국에서 배출된 이산화탄소가 한반도와 일본까지 영향을 미치고 있음을 확인할 수 있다. 그러나 이산화탄소의 유동은 인위적 배출원과 식생의 호흡, 해양의 배출과 흡수 등의 다양한 요인과 결부되어 달라지기 때문에 이산화탄소 유동에 개입되는 다양한 변수와 상관성을 평가하는 후속연구가 필요할 것으로 사료된다.

• 대한조선학회논문집
• /
• 제43권5호
• /
• pp.538-549
• /
• 2006

A code is developed to simulate a viscous flow field around a deformable body using the hybrid Cartesian/immersed boundary method. In this method, the immersed boundary(IB) nodes are defined near the body boundary then velocities at the IB nodes are reconstructed based on the interpolation along the normal direction to the body surface. A new method is suggested to define the IB nodes so that a closed fluid domain is guaranteed by a set of IB nodes and the method is applicable to a zero-thickness body such as a sail. To validate the developed code, the vorticity fields are compared with other recent calculations where a cylinder orbits and moves into its own wake. It is shown the code can handle a sharp trailing edge at Reynolds number of $10^5$ under moderate requirements on girds. Finally the developed code is applied to simulate the vortex shedding behind a deforming foil with flapping tail like a fish. It is shown that the acceleration of fluids near the flapping tail contributes to the generation of the thrust for propulsion.

• 한국추진공학회지
• /
• 제6권3호
• /
• pp.29-36
• /
• 2002

2차원, 3차원 비압축성 Navier-Stokes 방정식을 이용하여 DCA 압축기 익렬의 수치해석을 수행하고, 여러 가지 입사각에 대해 실험치와 비교.검토하였다. SIMPLE 알고리즘을 적용한 2차원, 3차원 코드는 대류항의 이산화에 하이브리드 도식을, 집중격자기법을 사용할 때 발생할 수 있는 압력진동해를 방지하기 위하여 PWIM을 사용하였다. 캐스케이드 유동을 예측하는데 있어서 가장 중요한 요소 중의 하나가 난류모델링이다. 이는 캐스케이드 내의 유동이 역압력구배에 의한 박리와 재부착 등의 복잡한 양상을 보이기 때문이다. 본 연구에서는 계산시간의 효율성을 고려해 $\kappa$-$\varepsilon$ 벽법칙 모델을 사용하였다.

• 대한의용생체공학회:의공학회지
• /
• 제20권1호
• /
• pp.29-36
• /
• 1999

본 연구는 목적은 PIV 시스템을 이용하여 분기관내 유동현상을 가시화하여 분기부 영역의 유동특성을 분석하는데 있다. PIV 시스템으로 유동장을 가시화하기 위해서 분기관 모델은 투명 아크릴판으로 제작하였고 작동유체와 추적입자는 각각 물과 송화가루를 사용하였다. 유동장에서 획득된 영상으로부터 속도벡터를 얻기 위해서 입자추적방법의 1-프레임 법과 2-프레임 법, 상호상관 PIV법인 2-프레임법을 사용하였다. PIV 시스템으로 측정된 실험결과의 신뢰성을 확보하기 위해서 표면구동 캐비티 유동의 속도분포를 4-프레임법으로 얻어진 기준 실험 데이터와 비교하였다. 분기관에서 뉴턴유체의 유동현상을 효과적으로 가시화하는데 필요한 상호상관 PIV방법의 2-프레임법을 적용하는 알고리즘을 개발하였고, sub-pixel과 면적보간을 사용하여 오벡터를 제거후 최종속도벡터를 얻었다. PIV를 이용한 분기관내 유동가시와 실험결과를 신뢰할 수 있는 수치해석 결과를 이용하여 검증한 결과 PIV 실험으로 얻어진 속도벡터는 수치해석의 결과와 잘 일치하였다. PIV 실험과 수치해석 결과로부터 분기관모델의 분기점 원위부에 재순환영역이 형성됨이 확인되었고 두 다른 방법을 이용한 재순환영역의 길이와 높이는 거의 동일하였다.