• International Journal of Aeronautical and Space Sciences
• /
• 제1권2호
• /
• pp.9-16
• /
• 2000

For aerodynamic design of missile bodies of non-circular cross-section, the combination of the slender body theory and the cross-flow analogy can hardly be applied owing to the lack of experimental data. An alternative is to utilize the Euler solution in the design stage. For enhanced accuracy, however, an adequate viscous correction is necessary to the Euler solution. In this work, such a procedure is examined to compensate the viscous effect by utilizing the concept of proportionality factor in cross-flow analogy. Predictions of aerodynamic coefficients combining the Euler solution and the viscous correction via proportionality factor are made for a missile body of elliptic cross-section. Results indicate that the present approach can be adopted in designing missile bodies of non-circular cross-sections.

• 한국전산유체공학회지
• /
• 제19권2호
• /
• pp.30-39
• /
• 2014

We report in this paper the analysis of the motion of a needle and a spring in a viscous fluid under the influence of gravitational force. Lateral shift as well as vertical motion of a needle falling in a viscous fluid has been observed from a simple experiment. We also observed the combined rotation and translation of a falling spring. The trajectory and velocity of the falling needle and the spring were obtained by using an image processing technique. We also conducted numerical simulation for both problems. For the falling-needle problem, we employed a theory; but it turns out that significant correction is required for the solutions to match the numerical and experimental data. For the falling spring problem various theoretical formula were tested for their justification, but none of the existing theories can successfully predict the numerical and experimental results.

• 한국항공우주학회지
• /
• 제42권12호
• /
• pp.1028-1036
• /
• 2014

연구에서는 MOC 및 CFD를 이용한 극초음속 노즐 설계 절차를 수립하였다. MOC를 이용하여 설계된 비점성 노즐 형상에 대하여, 점성 유체 전산 해석을 통하여 경계층 두께를 산출하여 노즐 형상을 보정하였다. 여러 가지의 경계층 두께 정의를 비교한 결과, 노즐 단면 최대 속력의 95% 속력을 가지는 경계층 두께의 정의가 설계 마하수를 가장 잘 만족하는 것으로 여겨진다. 노즐 설계과정은 MOC 설계에 대한 격자 형성, 비점성 해석 및 점성 해석, 경계층 보정 및 점성 해석에 의한 확인 및 결과 도출의 순서로 진행되며, 모든 과정은 자동 일괄 처리토록 작성되었다.

• 한국신재생에너지학회:학술대회논문집
• /
• 한국신재생에너지학회 2008년도 춘계학술대회 논문집
• /
• pp.307-310
• /
• 2008

Nonlinear Vortex Strength Correction Method is developed for improvement of vortex lattice method which can't calculate the separated flow conditions and the viscous effect. In this method, the vortex strength on the blade surface is determined by matching the lift force from vortex lattice method with the lift force from aerodynamic coefficients table as the same circulation is added to or subtracted from all chord wise vortices. For considering the nonlinearities due to the neighboring blade sections, sophisticated Newton-Rapson algorithm is applied. The validation of this method was done by comparing the simulations with the measurements on the NREL Phase-VI horizontal axis wind turbine(HAWT) in the NASA Ames wind tunnel under uniform conditions. This method gives good agreements with experiments in most cases.

• 지구물리와물리탐사
• /
• 제27권2호
• /
• pp.119-128
• /
• 2024

해양자력탐사는 다른 탐사법에 비해 측정이 간편하여 해저 지구조 및 광상자원 분포 등의 탐사에 개척자 탐사로 주요하게 사용되는 방법이다. 측정은 주로 해수면 견인 자력계와 선상 삼성분 자력계를 주로 사용하고 있다. 해수면 견인 자력계는 분해능이 높다는 장점이 있지만 독자적인 연구선을 사용해야 하고, 자기장의 세기 만 측정할 수 있는 반면, 선상 삼성분 자력계는 상대적으로 분해능이 낮지만 자기장의 벡터 삼성분을 측정할 수 있고 연구선을 단독으로 사용하지 않아도 자료를 획득할 수 있다는 큰 장점을 가지고 있다. 하지만, 선상 삼성분 자력계는 선박의 자성 영향으로 인해 측정된 자료의 까다로운 보정이 필요하다. 현재까지 다양한 방법론이 제시되었지만 점성자화의 영향으로부터 벡터 삼성분의 보정이 불가능하였다. 본 연구에서는 해수면 견인 총 자력계와 선상 삼성분 자력계를 동시에 획득하였을 경우, 회전행렬을 통하여 간단하게 선상 삼성분 자력계로 얻은 자료를 해수면 견인 자력계로 얻은 자료로 바꿔 줌으로써 선박의 점성자화 성분을 효과적으로 제거하여 벡터 삼성분 자력이상 자료를 근사하여 보정하는 방법을 고안하였다. 오차분석을 통해 약 7-25 nT의 오차가 발생한 것을 확인하였는데 이는 지자기 이상 벡터의 잔여성분과 이로부터 유도되는 점성자화의 영향으로 여겨진다. 이 방법은 해양지자기의 정확한 벡터성분을 제공함으로써 지자기 이상 벡터성분의 다양한 해석을 가능하게 할 뿐만 아니라, 판 이동 및 지질 구조 연구, 해양 자원 개발 등 탐사의 정확성 향상에 크게 기여할 것으로 기대된다.

• 산업기술연구
• /
• 제15권
• /
• pp.153-168
• /
• 1995

The purpose of this study is to develop a method for predicting the aerodynamic performance of the subsonic airfoils in the 2-dimensional, steady and viscous flow. For this study, the airfoil geometry is specified by adopting the longest chord line system and by considering local surface curvature. In case of the inviscid-incompressible flow, the analysis is accomplished by the linearly varying strength vortex panel method and the Karman-Tsien correction law is applied for the inviscid-compressible flow analysis. The Goradia's integral method and the Truckenbrodt integral method are adopted for the boundary layer analysis of the laminar flow and the turbulent flow respectively. Viscous and inviscid solutions are converged by the Lockheed iterative calculating method using the equivalent airfoil geometry. And the analysis of the seperated flow is performed using the Dvorak and Maskew's method as the basic method. The wake effect is also considered and its geometry expressed by the formula of Summey & Smith when no seperation occurs. A computational efficiency is verified by the comparison of the computational results with experimental data and by the shorter execution time.

• 한국전산유체공학회지
• /
• 제3권2호
• /
• pp.65-72
• /
• 1998

From the Boltzmann equation with BGK approximation, a gas-kinetic BGK scheme is developed and methods for its efficient calculation, using the convergence acceleration techniques, are presented in a framework of an implicit time integration. The characteristics of the original gas-kinetic BGK scheme are improved in order for the accurate calculation of viscous and heat convection problems by considering Osher's linear subpath solutions and Prandtl number correction. Present scheme applied to various numerical tests reveals a high level of accuracy and robustness and shows advantages over flux vector splittings and Riemann solver approaches from Euler equations.

• 유체기계공업학회:학술대회논문집
• /
• 유체기계공업학회 2000년도 유체기계 연구개발 발표회 논문집
• /
• pp.61-64
• /
• 2000

In order to analyse the effect of the fluid viscosity changes on the centrifugal pump, the computer simulation method and the performance correction chart are used. The centrifugal pump is designed using the traditional method, and the 3D computational grid is generated for the impeller and casing. Working fluids are water, high viscous oil and muddy water. The viscosity of muddy water is measured by the unsteady capillary tube viscometer. The pump performances are predicted well through the computer simulation. The performance curves of head and efficiency for oil and muddy water are decreased. The torques of oil and muddy water, which is calculated by performance correction chart are predicted at a lower value than the computer simulation.

• 에너지공학
• /
• 제26권1호
• /
• pp.9-22
• /
• 2017

A combined thermal and flow analysis was carried out to study the behavior and performance of a small, commercial LTD (Low-Temperature-Differential) heat engine. Laminar-flow solutions for annulus and channel flows were employed to estimate the viscous drags on the piston and the displacer and the pressure difference across the displacer. Temperature correction factors were introduced to account for the departure from the ideal heat transfer processes. The analysis results indicate that the work required to overcome the viscous drags on engine moving parts and to move the displacer is much smaller than the moving-boundary work produced by the power piston for temperature differentials in the neighborhood of $20^{\circ}C$ and engine speeds below 10 RPS. A comparison with experimental data reveals large degradations from the ideal heat transfer processes. Thus, heat-transfer devices inside the displacer cylinder are recommended.

• 대한기계학회논문집B
• /
• 제22권2호
• /
• pp.240-252
• /
• 1998

The purpose of this study is to develop a method for predicting the aerodynamic performance of the low speed airfoils in the 2-dimensional, steady and viscous flow. For this study, the airfoil geometry is specified by adopting the longest chord line system and by considering local surface curvature. In case of the inviscid incompressible flow, the analysis is accomplished by the linearly varying strength vortex panel method and the Karman-Tsien correction law is applied for the inviscid compressible flow analysis. The Goradia integral method is adopted for the boundary layer analysis of the laminar and turbulent flows. Viscous and inviscid solutions are converged by the Lockheed iterative calculating method using the equivalent airfoil geometry. The analysis of the separated flow is performed using the Dvorak and Maskew's method as the basic method. The wake effect is also considered by expressing its geometry using the formula of Summey and Smith when no separation occurs. The computational efficiency is verified by comparing the computational results with experimental data and by the shorter execution time.