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전상언(S.E. Jeon),박수형(S.H. Park),김상호(S.H. Kim),변영환(Y.H. Byun),이재우(J.W. Lee),정경진(K.J. Jung) 한국전산유체공학회 2009 한국전산유체공학회 학술대회논문집 Vol.2009 No.11
Laminar separation bubble and transitional flow over an airfoil are investigated at a moderate range of Reynolds numbers. In this research, a Reynolds-Averaged Navier-Stokes code is coupled with an empirical transition model that can predict transition onset points and the length of transition region. Without solving the boundary layer equations, approximated e-N method is directly applied to the RANS code and iteratively solved together. The computational results are compared with the experimental data for NACA0012 airfoil. Results of transition onset point and length are compared well with experimental and XFOIL prediction. In high angle of attack the present RANS results show better agreement than XFOIL results using the boundary layer equations.
전상언(S.E. Jeon),손미소(M.S Son),박수형(S.H. Park),김창주(C.J. Kim),강희정(H.J. Kang),김승범(S.B. Kim),김승호(S.H. Kim) 한국전산유체공학회 2011 한국전산유체공학회 학술대회논문집 Vol.2011 No.11
A Reynolds-Averaged Navier-Stokes code is simultaneously coupled with the transition transport model of Langtry and Menter and applied to the numerical prediction of aerodynamic performance of the designed airfoils. Numerical prediction results for KU112F and KU109C airfoils are validated by experimental data obtained from a transonic wind tunnel. Drag coefficients from the experiment are better correlated to the numerical prediction results using a transition transport model rather than the fully turbulent simulation results. Maximum lift coefficient and drag divergence at the zero-lift condition with Mach number are investigated to evaluate the aerodynamic performance of the designed airfoils. Numerical and experimental data show that both airfoils achieve better performance than the baseline airfoils.
단일 및 다단의 가스 터빈 블레이드의 2차원 단면 유동 해석
전상언(S.E. Jeon),문찬웅(C.W. Moon),박수형(S.H. Park),사정환(J.H. Sa),신정훈(J.H. Shin) 한국전산유체공학회 2017 한국전산유체공학회지 Vol.22 No.3
Numerical investigation on two-dimensional blades of axial gas turbine is presented. The mixing plane method is applied for the boundary condition for multi-stage analysis. This method can be applied if flow field is steady and flow variations are neglected in the pitch-wise direction. The computation results are validated with the experimental data and effects of turbulence models are investigated. The VKI results using a transition model show closer correlation with the experimental data than those with fully turbulent assumption. The transition model using transport equations is widely used at moderate Reynolds numbers. The accuracy and usefulness of flow analysis on two-dimensional unsteady turbine are assessed through the multi-stage validation with the mixing plane method.
로터 익형 KU109C 풍동시험 및 천이유동 해석결과의 검증
전상언(S.E. Jeon),사정환(J.H. Sa),박수형(S.H. Park),김창주(C.J. Kim),강희정(H.J. Kang),김승범(S.B. Kim),김승호(S.H. Kim) 한국전산유체공학회 2012 한국전산유체공학회지 Vol.17 No.1
Transition prediction results are validated with experimental data obtained from a transonic wind tunnel for the KU109C airfoil. A Reynolds-Averaged Navier-Stokes code is simultaneously coupled with the transition transport model of Langtry and Menter and applied to the numerical prediction of aerodynamic performance of the KU109C airfoil. Drag coefficients from the experiment are better correlated to the numerical prediction results using a transition transport model rather than the fully turbulent simulation results. Maximum lift coefficient and drag divergence at the zero-lift condition with Mach number are investigated. Through the present validation procedure, the accuracy and usefulness of both the experiment and the numerical prediction are assessed.
천이 전달 방정식을 이용한 진동하는 익형의 동적 실속의 해석
전상언(S.E. Jeon),사정환(J.H. Sa),박수형(S.H. Park),변영환(Y.H. Byun) 한국전산유체공학회 2014 한국전산유체공학회지 Vol.19 No.1
Numerical investigation on the dynamic stall over an oscillating airfoil is presented. A Reynolds-Averaged Navier-Stokes (RANS) equations are coupled with transition transport equations for the natural transition. Computational results considering the turbulent transition are compared with the fully turbulent computations and the experimental data. Results with transition prediction show closer correlation with the experimental data than those with the fully turbulent assumption, especially in the reattachment region.
압축성 모서리에서 유입류가 충격파와 난류 경계층의 상호작용에 미치는 영향
전상언(S.E. Jeon),박수형(S.H. Park),변영환(Y.H. Byun) 한국전산유체공학회 2012 한국전산유체공학회 학술대회논문집 Vol.2012 No.5
Two compression ramp problems are computed to investigate inflow effects on the shock wave / boundary layer interaction. A Reynolds-Averaged Navier-Stokes code and a boundary layer generation code are applied for the generation of inflow boundary conditions. The computation results are validated well with the experimental data and effects of varying displacement thickness and momentum thickness are investigated. Separation bubble size and shock wave location over the compression ramps are well correlated with the shape parameter.
이세민(S.M. Lee),사정환(J.H. Sa),전상언(S.E. Jeon),김창주(C.J. Kim),박수형(S.H. Park),정기훈(K.H. Chung) 한국전산유체공학회 2010 한국전산유체공학회지 Vol.15 No.2
Aerodynamic design optimization of rotor airfoil has been performed with advanced design method for improved aerodynamic characteristics of ONERA airfoils. A multiple response surface method is used to consider various requirements in rotor airfoil design. Shape functions for mean camber line are proposed to extend possible design domain. Numerical simulations are performed using KFLOW, a Navier-Stokes solver with shear stress transport turbulence model. The present design method provides favorable configurations for the high performance rotor airfoil. Resulting optimized airfoils give better aerodynamic performance than the baseline airfoils.
이세민(S.M. Lee),사정환(J.H. Sa),전상언(S.E. Jeon),김창주(C.J. Kim),박수형(S.H. Park),정기훈(K.H. Chung) 한국전산유체공학회 2010 한국전산유체공학회 학술대회논문집 Vol.2010 No.5
Aerodynamic design optimization of rotor airfoil has been performed with advanced design method for improved aerodynamic characteristics of ONERA airfoils as a baseline. A multiple response surface method is used to consider various constraints in rotor airfoil design. Airfoil surface and mean camber line are modified using various shape functions. Numerical simulations are performed using KFLOW, a Navier-Stokes solver with shear stress transport turbulence model. The present design method provides favorable configurations for the high performance rotor airfoil. Resulting optimized airfoils give better aerodynamic performance than the baseline airfoils.
사정환(J.H. Sa),전상언(S.E. Jeon),박수형(S.H. Park) 한국전산유체공학회 2014 한국전산유체공학회지 Vol.19 No.2
Two-dimensional prediction capability of several analysis codes, such as XFOIL, MSES, and KFLOW, is compared and analyzed based on computational results of airfoil flows. To this end the transition transport equations are coupled with the Navier-Stokes equations for the prediction of the natural transition and the separation-induced transition. Experimental data of aerodynamic coefficients are used for comparison with numerical results for the transitional flows. Numerical predictions using the transition transport model show a good agreement with experimental data. Discrepancies have been found in the prediction of the pressure drag are mainly caused by the difference in the far-field circulation correction methods.