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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.
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.
2차원 쐐기 형상의 자연 및 분사 공동의 비정상 유동 해석 연구
김진하(J.H. Kim),최요한(Y.H. Choi),김종암(C.A. Kim),정소원(S.W. Jeong),안병권(B.K. Ahn) 한국전산유체공학회 2017 한국전산유체공학회지 Vol.22 No.2
In this paper, the natural and ventilated cavitating flows behind a two-dimensional wedge is numerically investigated. In order to simulate the cavitation, we use multi-phase RANS flow solver with a homogeneous mixture model and a preconditioning technique. Good agreements are obtained between the present numerical results and the experiment for cavitating flow patterns, cavity length, and cavity pressure. Both cavitating flows show the characteristic of unsteady periodic vortical flow above certain cavitation number. The change of drag coefficients of a wedge by cavitation is also analyzed. Drag coefficients along with cavitation numbers change more by ventilated cavitation than natural cavitation. Compared to drag coefficients with no cavitation, drag coefficients are decreased by natural and ventilated cavitation. Ventilated cavitation can significantly decrease drag coefficients by changing pressure behind a wedge.
2-방정식 난류모델을 이용한 고양력 익형 주위의 비압축성/압축성 유동장 해석
김창성,김종암,노오현,Kim C. S.,Kim C. A.,Rho O. H. 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 incompressible 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 κ-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.