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김철완(C.W. Kim),이융교(Y.G. Lee),이대성(D.S. Lee) 한국전산유체공학회 2008 한국전산유체공학회지 Vol.13 No.2
For Aerodynamic analysis of vehicle at altitude, 100㎞, the validity of governing equations based on continuum model, was reviewed. Also, as the preliminary study for the sub-orbital space plane development, a candidate geometry was suggested and computational fluid dynamic(CFD) analysis was performed for various angles of attack in subsonic and supersonic flow regimes to analyze the aerodynamic characteristics and performance. The inviscid flow analyses showed that the stall starts at angle of attack above 20°, the maximum drag is generated at angle of attack, 87° and the maximum lift to drag ratio is about 8 in subsonic flow. In supersonic, the stall angle is about 40° and the maximum drag is generated at angle of attack, 90°. Also, mach number distribution of re-entry vehicle was computed versus altitudes.
김철완(C. W. Kim) 한국전산유체공학회 2011 한국전산유체공학회 학술대회논문집 Vol.2011 No.5
International energy agency(IEA) consisted of OECD countries deals with international energy problems. IEA/Wind ExCo is an execution committee under IEA for the implementing agreement for co-operation in the research, development and deployment of wind energy systems. Currently 22 countries participate the committee and 11 research tasks are in progress. 11 tasks are base technology information exchange, wind energy in cold climates, offshore wind energy technology deployment, integration of wind and hydropower systems, power systems with large amounts of wind power, cost of wind energy, labelling small wind turbines, social acceptance of wind energy projects, MexNext aerodynamics and comparison of dynamic computer codes and models, offshore wind energy and wakebench. At the presentation, activities of major wind energy countries and IEA/Wind ExCo and research tasks are introduced.
Navier-Stokes equations을 활용한 익형의 점성경계층 특성분석
김철완(C. W. Kim) 한국전산유체공학회 2011 한국전산유체공학회 학술대회논문집 Vol.2011 No.5
NACA0012 Airfoil was simulated with Computational Fluid Dynamics(CFD) and the aerodynamic characteristics was analyzed for various far-field boundary distances ranging from 10 airfoil chord to 50 chord. Drag coefficient distribution was dependent on the far-field distance and circulation, integrated along the loop inside the flow region, was also dependent. It was turned out that some corrections based on the circulation should be added to the far-field boundary condition for accurate airfoil simulation.
김철완(C.W. Kim),이융교(V.G. Lee) 한국전산유체공학회 2009 한국전산유체공학회 학술대회논문집 Vol.2009 No.4
In the present paper, transition turbulence model is applied to the NACA64(3)618. and detailed flow features are studied. The turbulence model is sensitive to the boundary layer grid quality and y+ oi the grid was limited to I. The prediction of the transition region is dependent on the local flow condition. The pressure coefficient distribution of the transition turbulence model is compared with that of the fully turbulent mode and the drag distribution of the transition turbulence model was compared with that of the wind tunnel test.
김철완(C. W. Kim) 한국전산유체공학회 2003 한국전산유체공학회지 Vol.8 No.3
A non-dissipative and very accurate one-dimensional upwind leapfrog method is extended to higher-order and multi-dimensional advection and acoustic equations. The higher-order versions are developed by extending the stencils in space and time. The schemes are then successfully applied to the classical test cases for advection and acoustics.
김철완(C.W. Kim),이융교(Y.G. Lee) 한국전산유체공학회 2007 한국전산유체공학회 학술대회논문집 Vol.2007 No.-
In the present paper, wall correction method is reviewed and applied to the numerical experimental results obtained at the wind tunnel condition. The corrected Iift coefficient agrees well with the reference data generated from the grid having very far boundary. However the corrected drag coeffcient presents some deviation from the reference data.