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RISS 인기검색어
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- 저자 : 김종암(C. Kim) (검색결과 79 건)
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2-방정식 난류모델을 이용한 고양력 익형 주위의 비압축성/압축성 유동장 해석
김창성(C. S. Kim),김종암(C. A. Kim),노오현(O. H. Rho) 한국전산유체공학회 1999 한국전산유체공학회지 Vol.4 No.1
Two-dimensional, unsteady, incompressible and compressible Navier-Stokes codes are developed for the computation of the viscous turbulent flow over high-lift airfoils. The compressible code involves a conventional upwind-differenced scheme for the convective terms and LU-SGS scheme for temporal integration. The incompressible code with pseudo-compressibility method also adopts the same schemes as the compressible code. Three two-equation turbulence models are evaluated by computing the flow over single and multi-element airfoils. The compressible and incompressible codes are validated by predicting the flow around the RAE 2822 transonic airfoil and the NACA 4412 airfoil, respectively. In addition, both the in?compressible and compressible code are used to compute the flow over the NLR 7301 airfoil with flap to study the compressible effect near the high-loaded leading edge. The grid systems are efficiently generated using Chimera overlapping grid scheme. Overall, the k-ω SST model shows closer agreement with experiment results, especially in the prediction of adverse pressure gradient region on the suction surfaces of high-lift airfoils.
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2-방정식 난류모델을 이용한 고양력 익형 주위의 비압축성/압축성 유동장 해석
김창성(C. S. Kim),김종암(C. A. Kim),노오현(O. H. Rho) 한국전산유체공학회 1999 한국전산유체공학회지 Vol.4 No.1
Two-dimensional, unsteady, incompressible and compressible Navier-Stokes codes are developed for the computation of the viscous turbulent flow over high-lift airfoils. The compressible code involves a conventional upwind-differenced scheme for the convective terms and LU-SGS scheme for temporal integration. The incompressible code with pseudo-compressibility method also adopts the same schemes as the compressible code. Three two-equation turbulence models are evaluated by computing the flow over single and multi-element airfoils. The compressible and incompressible codes are validated by predicting the flow around the RAE 2822 transonic airfoil and the NACA 4412 airfoil, respectively. In addition, both the in?compressible and compressible code are used to compute the flow over the NLR 7301 airfoil with flap to study the compressible effect near the high-loaded leading edge. The grid systems are efficiently generated using Chimera overlapping grid scheme. Overall, the k-ω SST model shows closer agreement with experiment results, especially in the prediction of adverse pressure gradient region on the suction surfaces of high-lift airfoils.
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초소형 비행체 주위의 저 레이놀즈수 영역에 대한 수치 해석 및 실험적 연구
김영훈(Y.H. Kim),김우례(W.R. Kim),김종암(C. Kim),노오현(O.H. Rho) 한국전산유체공학회 2002 한국전산유체공학회 학술대회논문집 Vol.2002 No.-
A three-dimensional incompressible Navier-Stokes solver is developed for the flow analysis around Micro Air Vehicle(MAV) designed by MACDL(Micro Aerodynamic Control and Design Lab), Seoul National Univ.. Validations of this solver are presented for two cases, first flow over the circular cylinder with infinite length, second flow over infinite wing witH wing section, E387 airfoil. Simultaneously, Wind Tunnel test is performed with Flatform Wire type six-component balance and model designed by MACDL. The numerical results are also examined through comparison with experimental data.
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