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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.
김영환(Y. H. Kim),이준희(J. H. Lee),전재혁(J. H. Jeon),김종암(C. Kim),신상준(S. J. Sh),김상용(S. Y. Kim) 대한기계학회 2015 대한기계학회 춘추학술대회 Vol.2015 No.11
This paper presents the design and experimental results of the insect-mimicking Flapping-Wing Micro Air Vehicle (FWMAV) mechanism utilizing a six-bar linkage. The designed mechanism enables to radically change the wing trajectory in limited fuselage spaces through a small alteration in the location of the joint. We mapped this wing trajectory in order to implement the concept of fully-controlled the FWMAV by using RecurDyn; a multi-body dynamics analysis software. The multi-body dynamic analysis allowed us to predict the amount of stress existing in each link prior to fabrication, enabling the construction of a more reliable component. As a result, possible operational errors during the production process were minimized. A test-bed was constructed to validate the assembled FWMAV’s performance, where the FWMAV’s aerodynamic forces and moments were confirmed through the experiment.