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신재렬,최정열 한국항공우주학회 2013 한국항공우주학회 학술발표회 논문집 Vol.2013 No.11
일반적인 코드 개발 과정에서 1차원 Euler 문제를 해석하여 수치기법의 정확성이나 수치기법의 특성을 이해할 수 있다. 1차원 Euler 문제에 다양한 수치 플러스 기법 및 고차 확장을 위한 해의 재구성법들의 조사하였다. 압력 차가 크지 않는 문제의 경우 고려하고 있는 수치 플럭스 기법, 고차 공간 정확도 기법과 제한자에서 계산이 잘 수행되었다. 고차정확도에 비해 저차의 경우 일정한 값으로 도달하는 시간이 긴 것으로 나타났다. 그러나 고차의 경우 일정한 값에 도달한 후에도 작은 진동이 포착되었다. 이 결과는 고차의 경우 해를 명확히 나타내고 저차는 매끄럽게 나타낸다는 것과 같은 의미를 나타낸다. We could understand an accuracy and feature of numerical schemes by solving 1-D Euler problems in general code development stage. We have investigated various numerical fluxes and reconstruction methods for high order special scheme with 1-D Euler problems. The results show that computing was carried out well in the case of less pressure difference of Reimann problems with considering numerical flux schemes, High order spatial schemes and limiters. Setting time of low order spatial scheme takes longer than high order spatial schemes to reach a certain value. However, after reaching a certain value in high order spatial schemes results, the value is small oscillated slightly. These results show high order spatial schemes are clearly resolved and low order spatial schemes are smoothly resolved.
추진기관시험설비에서 한국형발사체 추진기관 화염냉각의 수치적 연구
신재렬,김성룡,문성목 한국항공우주학회 2015 한국항공우주학회 학술발표회 논문집 Vol.2015 No.11
추진기관의 개발 및 인증을 위한 시험설비 구조물에 대한 화염냉각 시스템 설계 및 평가를 위해 추진기관의 화염냉가 해석을 수행하였다. 본 연구에는 상용 CFD 소프트웨어를 사용하여 냉각수인 물은 DPM 기법과 KHRT 2차분할 모델을 사용하여 수행하였다. 시험설비의 화염냉각 해석결과 시험설비가 화염으로부터 받는 열 하중을 충분히 견디는 것으로 평가되었다. The flame cooling analysis of propulsion system was carried out on the test facility structure for the design and evaluation of flame cooling system, this facility is for development and certification of a propulsion system. In this study, a commercial CFD software is used and the flame cooling simulation was carried out using DPM with KHRT 2nd breakup model for cooling water. From the results of flame cooling analysis of the test facility, it is evaluated enough endure thermal load from flame.
신재렬,김태우 한국항공우주학회 2021 International Journal of Aeronautical and Space Sc Vol.22 No.3
In this paper, a pressure-based coupled computational fluid dynamics algorithm for numerical analysis of all Mach number region flow is developed. For this purpose, an enhanced pressure based coupled algorithm was developed through the pressure–velocity coupled algorithm and the pressure-enthalpy coupled algorithm were combined. In additional, the Kurganov–Tadmor flux splitting scheme, which is mainly used in density-based solvers, was applied to a developed pressure-based coupled solver. To confirm the analytical ability of developed solver, the variety of Mach number flow problems were performed using the developed solver. It was confirmed that the developed solver had the similar analytical ability with that of the other numerical codes through the analysis of the shock tube problems. In order to verify the analytical ability for the variety Mach number flow region of the developed solver, 2D bump and nozzle problems and 3D missile and wing problems were analyzed and compared with results of experiments and other numerical analysis codes. It is confirmed that the analytical ability of developed solver in the all speed flow region is somewhat improved than the commercial analysis package and is similar to the density based in-house CFD code.