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김철완(C. W. Kim),정진덕(J. D. Chung),이장연(J. Y. Lee) 한국전산유체공학회 2004 한국전산유체공학회 학술대회논문집 Vol.2004 No.-
CFD simulation for Smart-UAV(TR-E2S1) is performed to analyze its aerodynamic characteristics. Base geometry and several cases, decided by control surfaces being deflected, are simulated. To obtain the better lift characteristics, the elevator should be deflected between 10o and 20o with the incidence angle of the wing 1o.
박영민(Y. M. Park),정진덕(J. D. Chung),김유신(Y. S Kim),최성욱(S. W. Choi) 한국전산유체공학회 2004 한국전산유체공학회 학술대회논문집 Vol.2004 No.-
Numerical optimization method of long endurance airfoil has been performed with a RSM(Response Surface Method) for smart UAV wing design. For the base line airfoil, NACA 64621 airfoil was selected and optimized to satisfy long endurance condition for smart UAV, Aerodynamic coefficients required for RSM are obtained by using 2-D Navier-Stokes solver with Spalart- Allmaras turbulence model. The optimized airfoil showed increased maximum lift and endurance factors together with reasonable thickness ratio.
박영민(Y.M. Park),정진덕(J.D. Chung),이해창(H.C. Lee) 한국전산유체공학회 2013 한국전산유체공학회 학술대회논문집 Vol.2013 No.5
The recent development of CFD technologies and computing resources enables high fidelity aircraft analysis and designs in even conceptual and preliminary design process. More and more, these high fidelity analysis are replacing the high cost wind tunnel tests and contributes to the reduction of entire aircraft design period. In the present paper, examples of CFD applications in KARI(Korea Aerospace Research Institute) are introduced especially for fixed wing aircraft such as turboprop. In KARI, most of CFD processes are mainly used for analysis and design of aircraft. The most basic approaches is for the design of two dimensional airfoil and high lift devices using Navier-Stokes solver. For the three dimensional wing analysis such as wing planform study, high lift device, Navier-Stokes simulations are also commonly used for low and high speed aerodynamic analysis. In order to analyze the effect of rotating propeller effect, unsteady Navier-Stokes simulations using sliding mesh technique are used for the relative motion. In the present paper, various applications of CFD in KARI for fixed wing aircraft design are introduced from two-dimensional high lift device design to rotating propeller effect including high lift device.
박영민(Y. M. Park),김철완(C. W. Kim),정진덕(J. D. Chung),이해창(H. C. Lee) 한국전산유체공학회 2011 한국전산유체공학회 학술대회논문집 Vol.2011 No.5
A rotating propeller of turboprop aircraft gives much effect on the aerodynamic characteristics of wing such as lift, moment and stall. Specially, a rotating propeller changes the lift and moment characteristics when aircrafts are in landing or take-off condition. In the present paper, 3-dimensional Navier-Stokes simulations for the interaction of propeller and wing were carried out. For rotating propeller, unsteady sliding mesh method was used to simulate a relative motion. For the power effect analysis in landing and take off configurations, double slotted flap was also considered and the aerodynamic characteristics were investigated. It was shown that the propeller slipstream enhanced the lift slope including maximum lift and this enhancement was more dominant with high lift device.
프로펠러와 고양력 장치와의 공력간섭에 대한 수치해석 연구
박영민(Y. M. Park),김철완(C. W. Kim),정진덕(J. D. Chung),이해창(H. C. Lee) 한국전산유체공학회 2011 한국전산유체공학회지 Vol.16 No.4
A rotating propeller of turboprop aircraft gives much effect on the aerodynamic characteristics of wing such as lift, moment and stall. Specially propeller effect on the wing surface is much more dominant when aircrafts are in landing or take-off conditions. In the present paper, three dimensional Navier-Stokes simulations for the interaction of propeller and wing were carried out for medium sized turboprop aircraft. For rotating propeller, unsteady sliding mesh method was used to simulate a relative motion between moving and static bodies. For the power effect analysis in landing and take off configurations, double slotted flap was also considered and the aerodynamic characteristics were investigated. It was shown that the propeller slipstream enhanced the lift slope including maximum lift by eliminating local flow separation region and this enhancement was more dominant with high lift device.