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비정렬 적응 격자계를 이용한 비정상 로터-동체 공력 상호작용 모사
남화진(H. J. Nam),박영민(Y. M. Park),권오준(O. J. Kwon) 한국항공우주학회 2005 韓國航空宇宙學會誌 Vol.33 No.2
3차원 비정렬 격자를 이용한 로터-동체 공력 상호작용에 대한 수치적 해석을 수행하였다. 로터와 동체간의 상대적인 운동을 모사하기 위하여 해석 유동장을 회전하는 부분과 정지된 부분으로 나누어 계산하였다. 블레이드 끝단에서 생성되는 끝단 와류를 포착하기 위하여 준 비정상 적응 격자 기법을 도입하였다. 또한 낮은 속도로 전진 비행하는 헬리콥터 해석을 위해서 저 마하수 예조건화 기법을 적용하였다. 로터-동체 공력 간섭현상에 대한 검증을 위해 Georgia Tech 형상과 NASA에서 실험한 ROBIN 형상에 대한 실험 결과와 비교하여 본 연구 해석 기법이 타당함을 보였다. A three-dimensional parallel Euler flow solver has been developed for the simulation of unsteady rotor-fuselage interaction aerodynamics on unstructured meshes. In order to handle the relative motion between the rotor and the fuselage, the flow field was divided into two zones, a moving zone rotating with the blades and a stationary zone containing the fuselage. A sliding mesh algorithm was developed for the convection of the flow variables across the cutting boundary between the two zones. A quasi-unsteady mesh adaptation technique was adopted to enhance the spatial accuracy of the solution and to better resolve the wake. A low Mach number pre-conditioning method was implemented to relieve the numerical difficulty associated with the low-speed forward flight. Validations were made by simulating the flows around the Georgia Tech configuration and the ROBIN fuselage. It was shown that the present method is efficient and robust for the prediction of complicated unsteady rotor-fuselage aerodynamic interaction phenomena.
항공기 형상 최적설계를 위한 표면 패널 격자 자동 생성 프로그램 개발
김경남(G.N. Gim),남화진(H.J. Nam),이성진(S.J. Lee),김병수(B.S. Kim) 한국전산유체공학회 2014 한국전산유체공학회 학술대회논문집 Vol.2014 No.11
This paper describes study results on the development of an automatic program for generating surface-panel grid for the aircraft optimal design. The aerodynamic analysis is combined into a PIDO tool in conjunction with a number of programs in order to integrate processes for the optimal design. Due to design optimization’s iterative feature, it may require lots of time and cost. To relieve this problem, cost-reduction of computation time for aerodynamic analysis is pursued by using the Panel-method, and reduction of grid generation time by automating surface panelling.
항공기 개념설계를 위한 공력 해석용 자동 표면 패널 격자 생성 프로그램 개발
김경남(G. N. Gim),남화진(H. J. Nam),김병수(B. S. Kim) 한국전산유체공학회 2014 한국전산유체공학회 학술대회논문집 Vol.2014 No.5
This paper describes the current status of our research on the development of a program that allows users to easily generate surface panels for fast aerodynamic analysis which can be used in the conceptual design phase of aircraft development. It takes advantage of the CATIA program for defining the shape of the aircraft, and the shape modeling module has been developed to produce aircraft model in the STL format files, and the paneling module produces a grid of the surface panels along the STL surface data. The resultant panel data are plugged into a commercial analysis code(e.g. USAERO program) for the fast and iterative flow calculation. The current approach can reduce the cost in terms of time and labor required in the earlier stage of aircraft development.
CATIA Automation 기법을 이용한 해석 모델의 최적화 및 형상 특성 데이터 추출에 대한 연구
장석(S. Chang),김경민(K.M. Kim),남화진(H.J. Nam),김병수(B.S. Kim) 한국전산유체공학회 2011 한국전산유체공학회 학술대회논문집 Vol.2011 No.11
This paper describes development of a computer program which can be used to aid geometry design and CAE process in the conceptual design phase of fighters. This program enables efficient generation of computational analysis model of the product which is cleaned with Air-Tightening technique by applying VBA-based automation programming as one of automation methods in the CATIA modelling environment. The program also generates Cross Section Area Curve data automatically as one of primary geometry-characteristic data for computational analysis in the early aircraft design phase.
김경남(G.M. Gim),손서빈(S.B. Son),남화진(H.J. Nam),이성진(S.J. Lee),김창민(C.M. Kim),김병수(B.S. Kim) 한국전산유체공학회 2013 한국전산유체공학회 학술대회논문집 Vol.2013 No.10
In this paper, surface grid generation program for aerodynamic analysis using panel method is described. This program can be used to generate Panel-grid along the body surfaces which are defined as STL data. STL format is one of those standard neutral formats for model data exchange. The program allows its user to define surface patches either interactively by manual mode or semi-automatically by automatic mode with proper amount of user-specified parameters. Users create the Panel-grid that there are no flow girds in order to quickly analyze aerodynamics. A panel method requires much less wall-clock time and human resources compared to conventional CFD approaches for flow analysis, and it is still widely used in the preliminary design stage for airplane design process. This research would suggest an efficient way of surface panel-generation for aircraft aerodynamic analysis.