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프로펠러 효과를 반영 가능한 패널 기반 신속 공력 해석 기법 개발
태명식(Myungsik Tai),이예빈(Yebin Lee),오세종(Sejong Oh),신정우(Jeongwoo Shin),임주섭(Joosup Lim),박동훈(Donghun Park) 한국항공우주학회 2021 韓國航空宇宙學會誌 Vol.49 No.2
전기동력 분산추진 비행체는 다수의 프로펠러로 인하여 복잡한 프로펠러 후류 유동 및 기체와의 상호간섭이 발생한다. 이에 따라 초기설계 단계에서는 다양한 형상과 비행 조건에 대하여 프로펠러 구동 효과를 반영한 신속 공력 및 하중 해석이 요구된다. 본 연구에서는 프로펠러 효과를 고려할 수 있는 패널 기반의 효율적인 공력해석 기법을 개발, 검증하였다. Actuator Disk Theory(ADT)에 기반하여 프로펠러 후류 영역의 유도 속도장을 계산하고, 이를 3차원 정상 용출-중첩 패널기법의 비행체 표면 경계조건에 반영하였다. 한국항공우주연구원의 Quad Tilt Propeller(QTP) 비행체 단독 프로펠러와 선행 실험 연구의 프로펠러-날개 형상을 벤치마크 문제로 선정하여 해석을 수행하였다. Actuator 기법 기반의 전산유체역학(CFD) 결과와의 비교를 통해 프로펠러의 후류 속도장과 프로펠러 구동에 따른 날개의 공력하중 분포 변화를 검증하였다. 자율비행 개인용 항공기(Optional Piloted PAV, OPPAV)와 QTP 공력해석에 기법을 적용하고, CFD와의 해석 소요 시간 및 결과 비교, 분석을 통해 기법의 실용성과 타당성을 확인하였다. Electric-powered distributed propulsion aircraft possess a complex wake flow and mutual interference with the airframe, due to the use of many propellers. Accordingly, in the early design stage, rapid aerodynamic and load analysis considering the effect of propellers for various configurations and flight conditions are required. In this study, an efficient panel-based aerodynamic analysis method that can take into account the propeller effects is developed and validated. The induced velocity field in the region of propeller wake is calculated based on Actuator Disk Theory (ADT) and is considered as the boundary condition at the vehicle’s surface in the three-dimensional steady source-doublet panel method. Analyses are carried out by selecting an isolated propeller of the Korea Aerospace Research Institute (KARI)’s Quad Tilt Propeller (QTP) aircraft and the propeller-wing configuration of the former experimental study as benchmark problems. Through comparisons with the results of computational fluid dynamics (CFD) based on actuator methods, the wake velocity of propeller and the changes in the aerodynamic load distribution of the wing due to the propeller operation are validated. The method is applied to the analysis of the Optional Piloted Personal Aerial Vehicle (OPPAV) and QTP, and the practicality and validity of the method are confirmed through comparison and analysis of the computational time and results with CFD.
초음속 조건의 플랩을 장착한 Busemann Biplane의 플랩 길이와 각도 변화에 따른 양항비 성능 비교
태명식(Myungsik Tai),손찬규(Chankyu Son),오세종(Sejong Oh) 한국전산유체공학회 2013 한국전산유체공학회지 Vol.18 No.3
The supersonic airplane with flapped biplane, Busemann biplane equipped flap, is superior to drag and noise reduction due to wave cancelation effect between upper and lower airfoils. In this study, it is numerically calculated and analyzed the lift, drag and lift to drag ratio of flapped biplane with respect to various the length and angle of the flap. Euler solver of EDISON CFD, web based computational fluid dynamic solver for the purpose of education, is employed. Depending on the length of the flap, lift and drag increase linearly, and there exists the optimum flap angle which maximize the lift-to-drag ratio at the freestream mach 2.0 on-design condition. The predictable relational expression is driven as liner equation. As a results of comparison with drag of flapped biplane, Busemann biplane, and diamond airfoil with the same lift, the drag of flapped biplane is 88.76% lower than that of the Busemann biplane and 70.67% lower than that of the diamond airfoil. In addition, the change of pressure is compared to confirm the noise reduction effect of flapped biplane at h/c=5 of lower airfoil. The shock strength of flapped biplane is smaller than that of other airfoils.