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Actuator 기법을 이용한 프로펠러 3축 성분 힘/모멘트 해석
이예빈(Y.B. Lee),이성기(S.G. Lee),오세종(S.J. Oh),최재훈(J.H. Choi),이융교(Y.G. Lee),조태환(T.H. Cho),박동훈(D.H. Park) 한국전산유체공학회 2020 한국전산유체공학회지 Vol.25 No.1
For aerodynamic performance and stability analysis of distributed propulsion aircraft which adopt many propellers/rotors, all the 3-axial components forces and moments must be properly taken into account. In this study, two actuator methods have been established to be capable of numerical simulations including all the force and moment components produced by rotor/propeller. A procedure in which the 3-axial components are transformed from the aerodynamic force and moment of blade elements has been added to actuator disk method(ADM) and actuator surface method(ASM). The numerical analyses are carried out for a single propeller of quad tilt propeller(QTP) at various flight conditions including the variation of side slip angle. The results are compared with wind tunnel test data and full CFD simulation with overset grid. All the force and moment components are found to agree very well in terms of engineering purposes and the present methods are identified to be numerically very efficient compared to full CFD. Power-on effect and longitudinal stability of the full configuration of QTP is further analyzed by carrying out the additional numerical simulations. The results indicate that the present methods is practically very useful to investigate the aerodynamic performance of distributed propulsion aircraft.
전산해석 및 풍동시험을 이용한 다기능 대기 자료 센서의 공력 설계
박영민(Y.M. Park),최인호(I.H. Choi),이융교(Y.G. Lee),권기정(K.J. Kwon),김성찬(S.C. Kim),황인희(I.H. Hwang) 한국전산유체공학회 2010 한국전산유체공학회지 Vol.15 No.3
Aerodynamic design of the vane type multi-function probe was tried by using CFD and wind tunnel test for the MALE UAV and small business jets. The present multi-function probe can measure total pressure, static pressure and angle of attack by using rotating vane. Therefore, major performances are determined by aerodynamic characteristics of vane. In order to design the sensor compatible to the requirement, aerodynamic characteristics of sensors were investigated by using CFD and dynamic response analysis was also performed for transient performance. The final aerodynamic performance was measured by the wind tunnel test at Aerosonic and the results were compared with the present design. The results showed that the aerodynamic design using the CFD can be successfully used for the design of vane type multi-function air data sensor.
박영민(Y.M Park),최인호(I.H. Choi),이융교(Y.G. Lee),권기정(K.J. Kwon),김성찬(S.C. Kim),황인희(I.H. Hwang) 한국전산유체공학회 2010 한국전산유체공학회 학술대회논문집 Vol.2010 No.5
Aerodynamic design of the vane type multi-function probe was tried by using CFD and wind tunnel test for the MALE UAV and small business jets. The present multi-function probe con measure total pressure, static pressure and angle of attack by using rotating vane. Therefore, major performances are determined by aerodynamic characteristics of vane. In oder to design the sensor compatible to the requirement, aerodynamic characteristics of sensors was investigated by using CFD and dynamic response analysis was also performed for transient performance. The final aerodynamic performance was measured by the wind tunnel test at Aerosonic and the results are compared with the present design. The results showed that the aerodynamic design using the CFD can be successfully used for the design of vane type multi-function air data sensor.
이광민(K.M. Lee),이융교(Y.K. Lee),김철완(C.W. Kim),안석민(S.M. Ahn) 한국전산유체공학회 2012 한국전산유체공학회 학술대회논문집 Vol.2012 No.11
This paper presents the computational aerodynamics analysis of a complete EAV(Electric Aerial Vehicle) configuration propeller rotating effect is applied. EAV-2H, being developed by KARI(Korea Aerospace Research Institute) is a technology demonstrator for HALE(High Altitude Long Endurance), solar energy and secondary battery is used to power this aircraft. Also it has been applied for long-endurance, high aspect ratio, low Reynolds airfoil. Computational analysis predicts the performance of the propeller and cruise power and it was verified by wind tunnel and flight tests.
김철완(C.W. Kim),이융교(Y.G. Lee),이대성(D.S. Lee) 한국전산유체공학회 2008 한국전산유체공학회지 Vol.13 No.2
For Aerodynamic analysis of vehicle at altitude, 100㎞, the validity of governing equations based on continuum model, was reviewed. Also, as the preliminary study for the sub-orbital space plane development, a candidate geometry was suggested and computational fluid dynamic(CFD) analysis was performed for various angles of attack in subsonic and supersonic flow regimes to analyze the aerodynamic characteristics and performance. The inviscid flow analyses showed that the stall starts at angle of attack above 20°, the maximum drag is generated at angle of attack, 87° and the maximum lift to drag ratio is about 8 in subsonic flow. In supersonic, the stall angle is about 40° and the maximum drag is generated at angle of attack, 90°. Also, mach number distribution of re-entry vehicle was computed versus altitudes.
김철완(C.W. Kim),이융교(Y.G. Lee) 한국전산유체공학회 2007 한국전산유체공학회 학술대회논문집 Vol.2007 No.-
In the present paper, wall correction method is reviewed and applied to the numerical experimental results obtained at the wind tunnel condition. The corrected Iift coefficient agrees well with the reference data generated from the grid having very far boundary. However the corrected drag coeffcient presents some deviation from the reference data.