• 한국전산유체공학회지
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• 제1권1호
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• pp.88-97
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• 1996

This paper treats an adaptive finite-element method for the viscous compressible flow governed by Navier-Stokes equations in two dimensions. The numerical algorithm is the two-step Taylor-Galerkin mettled using unstructured triangular grids. To increase accuracy and stability, combined moving node method and grid refinement method have been used for grid adaption. Validation of the present algorithm has been made by comparing the present computational results with the existing experimental data and other numerical solutions. Four benchmark problems are solved for demonstration of the present numerical approach. They include a subsonic flow over a flat plate, the Carter flat plate problem, a laminar shock-boundary layer interaction. and finally a laminar flow around NACA0012 airfoil at zero angle of attack and free stream Mach number of 0.85. The results indicates that the present adaptive triangular grid method is accurate and useful for laminar viscous flow calculations.

• 한국추진공학회지
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• 제7권2호
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• pp.15-22
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• 2003

본 연구에서는 2차원 압축성 Navier-Stokes 방정식을 사용하여 $30^{\cire}$ 경사진 터빈익의 냉각구를 통한 유출계수를 예측하였다. 내/외부 유동이 유출계수에 미치는 영향을 알아보기 위하여 외부유동만 존재하는 경우, 내부유동만 존재하는 경우 그리고 내/외부 유동이 없는 3가지 경우에 대하여 수치해석을 수행하였으며. 실험결과와 비교하였다. 본 연구의 수치해석결과는 유출계수를 잘 예측하였으며, 외부유동은 유출계수를 감소시키고, 내부유동은 냉각구내에서의 전압손실과 경계층의 영향을 감소시켜 특정 구간에서 유출계수를 증가시킨다는 것을 알았다.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2001년도 추계학술대회논문집B
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• pp.652-657
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• 2001

Computational work using the axisymmetric, compressible, Navier-Stokes Equations is carried out to predict the discharge coefficient of mass flow through a micro-critical nozzle. Several kinds of turbulence models and wall functions are employed to validate the computational predictions. The computed results are compared with the previous experimented ones. The present computations predict the experimental discharge coefficients with a reasonable accuracy. It is found that the standard $k-\varepsilon$ turbulence model with the standard wall function gives a best prediction of the discharge coefficients. The displacement thickness of the nozzle wall boundary layer is evaluated at the nozzle throat and is well compared to a prediction obtained by an empirical equation. The resulting displacement thickness of the wall boundary layer is about 2% to 0.6% of the diameter of the nozzle throat for the Reynolds numbers of 2000 to 20000.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2003년도 추계학술대회
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• pp.538-543
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• 2003

Perforated wall has long been employed to control a variety of flow phenomena. It has been, in general, characterized by a porosity of the perforated wall. However, this porosity value does not take account of the number and detailed shape of porous holes, but is defined by only the ratio of the perforated area to total wall surface area. In order to quantify the porous wall effects on the flow control performance, an effective porosity should be known with the detailed flow properties inside the porous holes. In the present study, a theoretical analysis using a small disturbance method is performed to investigate detailed flow information through porous hole and a computational work is also carried out using the two-dimensional, compressible Navier-Stokes equations. Both the results are compared with existing experimental data. The gasdynamical porosity is defined to elucidate the effect of perforated wall.

• 유체기계공업학회:학술대회논문집
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• 유체기계공업학회 2003년도 유체기계 연구개발 발표회 논문집
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• pp.167-173
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• 2003

For the measurement of mass flow rate at a wide range of operation conditions, it is required that the critical nozzle gas different diameters, since the mass flow rate through the critical nozzle depends on the nozzle supply conditions and the nozzle throat diameter. In the present study, both computational and experimental investigations are performed to explore the variable critical nozzle. Computational work using the 2-dimensional, axisymmetric, compressible Navier-Stokes equations are carried out to simulate the gas flow through variable critical nozzle. In experimnet, a cylinder with several different diameters is inserted into the critical nozzle to vary the nozzle throat diameter. Computational results are compared with the experimented ones. The computed results are in close agreement with experiment. It is found that the displacement and momentum thickness of variable critical nozzle are given as a function of Reynolds numbers. The discharge coefficient of the variable critical nozzle is predicted using an empirical equation.

• 대한기계학회논문집
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• 제12권1호
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• pp.106-115
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• 1988

본 연구에서는 경계층 유동을 충류, 천이, 난류 영역을 포함하는 압축성 유동으로 가정하였고, Morgan 등이 제시한 새로운 질점분할 방법을 사용하여 속도분포를 계산하고, 점성 압축성 효과를 고려하기 위하여 viscous--inviscid interaction 법을 사용하였고 이 계산 결과를 기존의 실험값과 비교하여,타당성을 확인하였다.그리고 최적 양력의 익형 설계는 Augmented Lagrange multiplier 법을 사용하였고 비구속 조건을 갖는 목적함수 augmented lagrangian의 최소화는 Davidan-Fletcher-Powell 방법 중 self-scaling quasi-Newton algorithm을 사용하였다. 그리고 NACA 23012를 기본 익형으로 하고 NACA 64-2-415, NACA 64-2-A215, NACA 65-3-218를 보상 익형으로 하여 최대 양력익형을 설계 하였다.

• 대한기계학회논문집B
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• 제41권9호
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• pp.615-622
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• 2017

충격파관에서 발생하는 충격파는 저압관단으로 전파하며, 관단에서 반사한다. 반사 충격파와 경계층의 간섭으로 반사 충격파에 분지가 발생하게 되고, 분지한 반사 충격파는 접촉면과 간섭하며, shock train이 발생하게 된다. 그러나 충격파관에서 발생하는 shock train 현상에 대한 연구는 미흡한 실정이다. 본 연구에서는 2차원 축대칭 충격파관을 사용하여 비정상, 압축성 Navier-Stokes 방정식을 적용한 수치해석을 수행하였으며, shock train의 상세한 특성을 조사하기 위하여, 고정된 압력비에서 충격파관의 길이 및 직경을 변화시켰다.

• 대한지질공학회:학술대회논문집
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• 대한지질공학회 2002년도 정기총회 및 학술발표회
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• pp.183-191
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• 2002

울산단층대 동변인 경북 경주시 마동 탑골 부근에 발달하는 제4기단층을 기재한다. 이 단층(이후 탑골단층)은 제3기초의 화강암과 제4기의 하성 사력층의 경계부 부근에서 여러 조의 단층들이 단층대를 이루며, 북북서 내지 남-북의 주향에 동측으로 $20^{circ}{\;}~45^{\circ}$ 의 경사를 보인다. 이 단층대는 서측으로부터 제4기 사력층 내의 역단층 3조와 제4기층을 화강암과 이를 부정합으로 덮는 제4기층이 올라탄 역단층 1조로 구별되며, 복합적인 역단층성 단층대의 양상을 보인다. 단층조선은 남동 방향($125^{\circ}$)으로 $20^{\circ}$ 침강한다. 이는 남동-북서 압축에 기인한 역단층성운동에 의해 생성된 것으로 보인다. 이 단층대는 불국사 일원에서 이미 알려진, 보다 서편에 발달하는 북서-남동 방향의 제4기단층선과는 다른 또 하나의 제4기단층선으로 확인된다.

• 대한기계학회논문집
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• 제19권9호
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• pp.2283-2296
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• 1995

Experiments of normal shock wave/turbulent boundary layer interaction were conducted in a supersonic diffuser. The flow Mach number just upstream of the normal shock wave was in the range of 1.10 to 1.70 and Reynolds number based upon the turbulent boundary layer thickness was varied in the range of 2.2*10$^{[-994]}$ -4.4*10$^{[-994]}$ . The wall pressures in streamwise and spanwise directions were measured for two test cases, in which the turbulent boundary layer thickness incoming into the supersonic diffuser was changed. The results show that the interactions of normal shock wave with turbulent boundary layer in the supersonic diffuser can be divided into three patterns, i.e., transonic interaction, weak interaction and strong interaction, depending on Mach number. The weak interactions generate the post-shock expansion which its strength is strong as the Mach number increases and the strong interactions form the pseudo-shock waves. From the spanwise measurements of wall pressure, it is known that if the flow Mach number is low, the interacting flow fields essentially appear two-dimensional, but they have an apparent 3-dimensionality for the higher Mach numbers.

• 한국가시화정보학회지
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• 제8권3호
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• pp.56-62
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• 2010

The interaction patterns between shock wave and boundary layer in a rocket nozzle are mainly classified into two categories, FSS(Free Shock Separation) and RSS(Restricted Shock Separation), both of which are associated with the thrust characteristics as well as side loads of the engine. According to the previous investigations, strong side loads of the engine are produced during the period of transition from FSS to RSS or vice versa. The present work aims at investigating the unsteady behavior of the separation shock waves in a two-dimensional supersonic nozzle, using experimental method and CFD. Schlieren optical method was employed to visualize the time-mean and time-dependent shock motions in the nozzle. The unsteady, compressible N-S equations with SST K-$\omega$ turbulence closure were solved using a fully implicit finite volume scheme. The results obtained show the separation shock motions during the transition of the interaction pattern.