A Corpus-based Study of the Particle up in the Korean High School Students Writing

The present study investigates Korean high school students usage of phrasal verbs containing the particle up by comparing their writing with English native speakers writing. The results indicate that, overall, Korean high school learners use this combination with similar degrees of frequency compared to their English native speaker counterparts, but that the two groups differ in regard to the variety of verbs. In addition, whereas the Korean high school learners demonstrated a marked preference for very idiomatic phrasal verbs, the English native speaker group employed a range of less idiomatic phrasal verbs. Analysis of the meaning of the particle up shows that there are fewer instances of aspectual meaning in the Korean learner corpora. Furthermore, give up, the most commonly appearing phrasal verb containing the particle up in Korean high school learners writing, is employed to express a limited number of meanings when compared with the English native speakers writing. In terms of pedagogical implications, the results suggest that the directional and aspectual meanings of particles should be taught. This will assist Korean high school learners in more effective use of phrasal verbs in their writing

Flow separation and nozzle side load simulations for TOP nozzle

OAIID:RECH_ACHV_DSTSH_NO:A201702754RECH_ACHV_FG:RR00200003ADJUST_YN:EMP_ID:A001138CITE_RATE:FILENAME:TC1-1.pdfDEPT_NM:기계항공공학부EMAIL:[email protected]_YN:FILEURL:https://srnd.snu.ac.kr/eXrepEIR/fws/file/5fdd5d4c-5c7c-4442-a51e-5c6eab6c8e04/linkCONFIRM:

The study of data transfer method between non-matching meshes interface using common-refinement method for fluid-structure interaction

본 연구는 유체-고체 연성 해석이 활발히 진행되고 있는 고체로켓의 3차원 연소실 상경계면 형상에 대해 정보 전달 기법 중 하나인 common-refinement 기법의 적용을 목적으로 수행되었다. 기법 구현은 상경계면에 common surface를 구성하고 특정 error norm을 최소화 시키는 minimization 내삽법을 적용하는 과정으로 수행되었다. 이를 바탕으로 다양한 다차원 상경계면 형상에서 연속 및 불연속 함수를 이용한 정보 전달 실험을 수행하였고, 다른 기법들과 해석 결과를 비교하였다.During multi-physics or multi-phase simulations accompanying fluid-structure thermal interaction, data transfer problems always arise along non-matching interfaces caused by different computational meshes for each physical domain. Common-refinement scheme, among many available methods, is attractive since it is known to yield conservative and accurate data transfer for non-matching interface cases. This is particularly important in simulating compressible unsteady fluid-structure thermal interaction inside solid propellant rockets, where grid size along solid-fluid interfaces is substantially different. From this perspective, we examine performances of common-refinement-based data transfer scheme between structured quadrilateral (structure part) and unstructured triangular (fluid part) meshes by comparing computed results with other data transfer methods.본 연구는 교육과학기술부의 우주기초원천기술 개발 사업(NSL, National Space Lab, No. 2011-0029871) 및 2012년도 정부(교육과학기술부) 의 재원으로 국가수리과학연구소의 주요사업 (No. A21001)으로부터 지원을 받아 이루어졌음OAIID:oai:osos.snu.ac.kr:snu2012-01/104/0000004648/35SEQ:35PERF_CD:SNU2012-01EVAL_ITEM_CD:104USER_ID:0000004648ADJUST_YN:NEMP_ID:A001138DEPT_CD:446CITE_RATE:0FILENAME:유체-구조_연성_해석을_위한_common-refinement_기반_불일치_격자_경계면에서의_정보_전달_기법_연구.pdfDEPT_NM:기계항공공학부EMAIL:[email protected]:

Full burning ALE based Fluid-Structure-combustion Interaction simulation for solid propellant rocket interior

A fluid-structure interaction simulation of solid propellant rocket interior is carried out by employing the ALE (Arbitrary Lagrangian Eulerian) description, a hybrid model of continuum motion description combining the advantages of classical Lagrangian and Eulerian description. The integration process for fluid-structure interaction and an automatic re-meshing algorithm are included to analyze an unsteady fluid-structure interaction phenomenon with the deformation of solid grain during the simulation. The developed solver is applied for the full burning simulation of a solid propellant grain, which is a highly-coupled unsteady phenomenon between gas flow and propellant structure. Based on the integrated computed results, flow physics in the combustion chamber and the behavior of a solid propellant deformation are examined.OAIID:oai:osos.snu.ac.kr:snu2013-01/104/0000004648/3SEQ:3PERF_CD:SNU2013-01EVAL_ITEM_CD:104USER_ID:0000004648ADJUST_YN:NEMP_ID:A001138DEPT_CD:446CITE_RATE:0FILENAME:2013우주발사체기술심포지움_한상호.pdfDEPT_NM:기계항공공학부EMAIL:[email protected]:

FSbI simulation for solid propellant rocket interior with flame propagation delay and secondary burning

A fluid-structure interaction simulation of solid propellant rocket interior is carried out by employing the ALE (Arbitrary Lagrangian Eulerian) description, a hybrid model of continuum motion description combining the advantages of classical Lagrangian and Eulerian description. The integration process for fluid-structure interaction and an automatic re-meshing algorithm are included to analyze an unsteady fluid-structure interaction phenomenon with the deformation of solid grain during the simulation. The developed solver is applied for the simulation of a solid propellant grain with inviscid/viscous fluid model. Based on the integrated computed results, flame propagation delay and secondary burning phenomena are examined from the physical and numerical perspectives.OAIID:oai:osos.snu.ac.kr:snu2014-01/104/0000004648/12SEQ:12PERF_CD:SNU2014-01EVAL_ITEM_CD:104USER_ID:0000004648ADJUST_YN:NEMP_ID:A001138DEPT_CD:446CITE_RATE:0FILENAME:고체 로켓 내부 fsbi.pdfDEPT_NM:기계항공공학부CONFIRM:

The study of data transfer method non-matching meshes interface using common-refinement method for fluid-structure interface

본 연구는 유체-고체 연성 해석이 활발히 진행되고 있는 고체로켓의 3차원 연소실 상경계면 형상에 대해 정보 전달 기법 중 하나인 공통세분 기법의 적용을 목적으로 수행되었다. 본 기법은 불일치하는 경계면간 정보 전달에도 보존성과 정확도를 동시에 만족시킬 수 있다는 장점을 갖는다. 기법 구현은 상경계면에 공통표면을 구성하고 특정 오차를 최소화 시키는 최소화 내삽법을 적용하는 과정으로 수행되었다. 이를 바탕으로 다양한 다차원 상경계면 형상에서 연속 및 불연속 함수를 이용한 정보 전달 실험을 수행하였고, 다른 기법들과 해석 결과를 비교하였다.During multi-physics or multi-phase simulations accompanying fluid- structure- thermal interaction, data transfer problems always arise along non- matching interfaces caused by different computational meshes for each physical domain. Common- refinement scheme, among many available methods, is attractive since it is known to yield conservative and accurate data transfer for non- matching interface cases. This is particularly important in simulating compressible unsteady fluid- structure- thermal interaction inside solid propellant rockets, where grid size along solid- fluid interfaces is substantially different. From this perspective, we examine performances of common- refinement- based data transfer scheme between structured quadrilateral (structure part) and unstructured triangular (fluid part) meshes by comparing computed results with other data transfer methodsOAIID:oai:osos.snu.ac.kr:snu2014-01/102/0000004648/1SEQ:1PERF_CD:SNU2014-01EVAL_ITEM_CD:102USER_ID:0000004648ADJUST_YN:YEMP_ID:A001138DEPT_CD:446CITE_RATE:0FILENAME:유체-구조_연성_해석을_위한_common-refinement_기반_불일치_격자_경계면에서의_정보_전달_기법_연구.pdfDEPT_NM:기계항공공학부SCOPUS_YN:NCONFIRM:

Atomic Layer Deposition of TiO2 Thin Films on Stainless Steel and its Photocatalytic Effects

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