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손미소(M. S. Son),박수형(S. H. Park) 한국전산유체공학회 2014 한국전산유체공학회 학술대회논문집 Vol.2014 No.5
Unsteady RANS computation was conducted to investigate vortical flow over the ONERA 70-degree delta wing at a high angle of attack. Using k-w shear-stress transport(SST) and Spalart-Allmaras(SA) turbulence model, a comparative study is presented with experimental data on the same grid and computation condition. SA model predicts well the pressure coefficient distribution. whereas the axial velocity and vorticity variation along the vortex core are not well predicted with the SA model.
고 받음각 ONERA 70도 삼각날개 와류 유동의 압력 섭동 분석
손미소(M. S. Son),사정환(J. H. Sa),박수형(S. H. Park),변영환(Y. H. Byun) 한국전산유체공학회 2015 한국전산유체공학회지 Vol.20 No.2
Delayed Detached-Eddy Simulation was conducted to investigate surface pressure coefficient distribution and surface pressure fluctuation over an ONERA 70-degree delta wing at a high angle of attack. Time-averaged surface pressure distribution is directly affected by the primary vortices, whereas the pressure fluctuation is influenced by the unsteady fluctuating boundary layer over the surface. And pressure coefficient, velocity, pressure fluctuation, and turbulent kinetic energy were analyzed along the vortex core in order to investigate the process of vortex breakdown. Consequently, strong pressure fluctuations were found where the vortex breakdown was occurred at x~620 mm. The turbulent kinetic energy abruptly increased and followed after the vortex breakdown.
70도 삼각날개 와류유동의 비정상 RANS 해석 결과 분석
손미소(M. Son),사정환(J. H. Sa),박수형(S.H. Park),구기범(G. Gu),김민아(M. Kim),정경진(K. J. Jung) 한국전산유체공학회 2013 한국전산유체공학회 학술대회논문집 Vol.2013 No.5
Unsteady RANS simulations were conducted in order to understand the physics of vortex flow over a delta wing at a high angle of attack. The feasibility and the accuracy of computational results were assessed through comparative study between computational and experimental data for ONERA 70-degree delta wing. Unsteady flow analysis showed a good agreement with experimental data in axial velocity and vorticity distributions. The vortex breakdown can be successfully traced by using the unsteady RANS simulation.
고받음각 델타익 유동의 와류 붕괴 모사를 위한 DES 해석
사정환(J.H. Sa),손미소(M. Son),박수형(S.H. Park),구기범(G. Gu),김민아(M. Kim),정경진(K.J. Jung) 한국전산유체공학회 2013 한국전산유체공학회 학술대회논문집 Vol.2013 No.5
Detached Eddy Simulation(DES) is performed to understand vortex breakdown of a high-angle-of-attack Delta Wing flow. The fifth-order Upwind method is used to reduce turbulent dissipation. The computational results(DES) on ONERA Delta Wing model with a 70° sweep angle are compared with unsteady Reynolds-averaged Navier-Stokes(RANS) results and experimental data for validation with pressure distribution, surface pressure coefficient contour, and streamline distribution.
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.