• 한국항공우주학회지
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• 제31권1호
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• pp.42-48
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• 2003

Lever II 헬리콥터 비행운동 방정식으로부터 주기성 트림해를 구하기 위해 DAE 해법에 근거한 PPTA(Partial Periodic Trimming Algorithm)를 제안하였다. PPTA의 반복계산으로 수정된 상태변수는 적합한 초기조건이 요구되는 DAE해법에서 수치불안정을 일으킬 수 있다. 간단하게 DAE 차수를 조절함으로써 정확한 주기성 트림을 얻을 수 있었다. 수치해법을 CBM(Common Baseline Model) 헬리콥터에 적용하여 harmonic balance 방법과 동일한 트림해를 얻었으며 시뮬레이션 초기의 과도응답을 효과적으로 제거할 수 있음을 밝혔다.

• 한국해안해양공학회:학술대회논문집
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• 한국해안해양공학회 2004년도 학술발표논문집 Proceedings of Coastal and Ocean Engineering in Korea
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• pp.264-268
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• 2004

• Journal of applied mathematics & informatics
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• 제8권1호
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• pp.27-44
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• 2001

A fast Poisson solver on irregular domains, based on bound-ary methods, is presented. The harmonic polynomial approximation of the solution of the associated homogeneous problem provides a good practical boundary method which allows a trivial parallel processing for solution evaluation or straightfoward computations of the interface values for domain decomposition/embedding. AMS Mathematics Subject Classification : 65N35, 65N55, 65Y05.

• Journal of applied mathematics & informatics
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• 제6권1호
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• pp.65-78
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• 1999

We present a fast/parallel Poisson solver on disks, based on efficient evaluation of the exact solution given by the Newtonian potential and the Poisson integral. Derived from an integral formula-tion it is more accurate and simpler in parallel implementation and in upgrading to a higher order algorithm than an algorithm which solves the linear system obtained from a differential formulation.

• 한국수자원학회논문집
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• 제37권10호
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• pp.845-855
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• 2004

본 연구에서는 수치모형을 이용하여 근해지진해일의 처오름 현상과 전파양상을 이용하여 해석하였다. 모의에 사용된 수치모형은 지진해일 거동의 해석에 적합한 비선형 천수방정식을 지배방정식으로 채택하였으며, 유한체적법을 이용하여 해석영역을 이산화 하였고 Riemann 문제를 해석하기 위하여 HLLC approximate Riemann solver와 Weighted Averaged Flux 기법을 이용하였다. 수치모형의 검증을 위하여 마찰 없는 수조에서의 수면진동문제와 원형섬 주위에서 고립파의 진행과 처오름에 대한 문제에 적용하여 각각 해석해 및 실험결과와 비교하였다. 수치모형에 의한 결과는 해석해와 수리모형실험 관측자료와 잘 일치하였다.

• 대한기계학회논문집
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• 제19권2호
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• pp.374-381
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• 1995

In this paper, integration methods for stiff constrained mechanical systems are studied to analyze dynamic response of the stiff mechanical system efficiently. The stiff, non-stiff systems are identified by using eigenvalues of the Jacobian of the systems. To integrate both stiff system and non-stiff system efficiently a new switching method between the non-stiff differential equation solver and the stiff differential equation solver is presented.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 1997년도 추계 학술대회논문집
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• pp.66-72
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• 1997

Circular-to-rectangular transition ducts are used as exhaust components of high performance fighter aircraft with vectored thrust nozzles. Three-dimensional incompressible Navier-Stokes solver is used to analyze the transition duct. Cross sections of transition duct are defined by superelliptic equation. The grid system is generated by Non-Uniform Rational B-Spline, after generating surface grid by blending the cross sections. Good agreement between the results of the computational simulation and the experimental data is observed.

• Water Engineering Research
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• 제4권4호
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• pp.175-185
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• 2003

A numerical model to analyze dam break flows has been developed based on approximate Riemann solver. The governing equations of the model are the nonlinear shallow-water equations. The governing equations are discretized explicitly by using finite volume method and the numerical flux are reconstructed with weighted averaged flux (WAF) method. The developed model is verified. The first verification problem is about idealized dam break flow on wet and dry beds. The second problem is about experimental data of dam break flow. From the results of the verifications, very good agreements have been observed

• Journal of applied mathematics & informatics
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• 제19권1_2호
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• pp.215-229
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• 2005

In this paper, constraint aggregation is combined with the adjoint and multiple shooting strategies for optimal control of differential algebraic equations (DAE) systems. The approach retains the inherent parallelism of the conventional multiple shooting method, while also being much more efficient for large scale problems. Constraint aggregation is employed to reduce the number of nonlinear continuity constraints in each multiple shooting interval, and its derivatives are computed by the adjoint DAE solver DASPKADJOINT together with ADIFOR and TAMC, the automatic differentiation software for forward and reverse mode, respectively. Numerical experiments demonstrate the effectiveness of the approach.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 1999년도 추계 학술대회논문집
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• pp.167-173
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• 1999

An Euler-based CFD tool has been developed for the performance evaluation of a thrust reverser mounted on a high bypass ratio turbofan engine. The computational domain surrounded by the ground and non-reflection boundary includes the whole nacelle configuration with a deployed thrust reverser. The numerical algorithm is based on the modified Godunovs scheme to allow the second order accuracy in both space and time. The grid system is generated by using eleven multi-blocks, of which the total cell number is 148,400. The thrust reverser is modeled as if it locates at the nacelle simply in all circumferential direction. The existence of a fan and an OGV(Outlet Guide Vane) is simulated by adopting the actuator disk concept, in which predetermined radial distributions of stagnation pressure ratio and adiabatic efficiency coefficient are used for the rotor type disk, and stagnation pressure losses and flow outlet angles for the stator type disk. All boundary conditions including the fan and OGV simulation are treated by Riemann solver. The developed solver is applied to a turbofan engine with a bypass ratio of about 5.7 and the diameter of the fan cowl of 83 inch. The computational results show that the Euler-based inviscid method is very useful and economical to evaluate the performance of thrust reversers.