SEPARATION CONTROL USING SYNTHETIC JET ON NACA23012 AT HIGH ANGLE OF ATTACK

Flow control has been performed using synthetic jet on NACA23012. In order to improve aerodynamic performance, synthetic jet is located near separation point on airfoil with leading edge droop and plain flap. The flow control using synthetic jet shows that stall characteristics and control surface performance can be improved through resizing separation vortices. Stall is delayed and stall characteristics are improved when synthetic jet is applied from separation region of leading edge droop. Control surface effectiveness is increased and lift is increased when synthetic jet applied at the flap leading edge region. The results show that aerodynamic characteristics can be improved through leading edge droop with synthetic jet at near separation and plain flap with synthetic jet at the flap leading edge. The combination of synthetic jet and simple high lift device is as good as fowler flap system.OAIID:oai:osos.snu.ac.kr:snu2005-01/104/0000004648/21SEQ:21PERF_CD:SNU2005-01EVAL_ITEM_CD:104USER_ID:0000004648ADJUST_YN:NEMP_ID:A001138DEPT_CD:446CITE_RATE:0FILENAME:고받음각의_NACA23012익형에서_synthetic_jet을_이용한_박리_제어_연구.pdfDEPT_NM:기계항공공학부EMAIL:[email protected]:

A COMPARATIVE STUDY BETWEEN DISCONTINUOUS GALERKIN AND SPECTRAL VOLUME METHODS ON STRUCTURED GRIDS

Conventional high order interpolation schemes are limitative in several aspects mainly because they need data of neighboring cells at the reconstruction step. However, discontinuous Galerkin method and spectral volume method, two high order flux schemes which will be analyzed and compared in this paper, have an important benefit that they are not necessary to determine the flow gradients from data of neighboring cells or elements. These two schemes construct polynomial of variables within a cell so that even near wall or discontinuity, the high order does not deterioratOAIID:oai:osos.snu.ac.kr:snu2005-01/104/0000004648/36SEQ:36PERF_CD:SNU2005-01EVAL_ITEM_CD:104USER_ID:0000004648ADJUST_YN:NEMP_ID:A001138DEPT_CD:446CITE_RATE:0FILENAME:2차원_정렬_격자계에서의_불연속_갤러킨_기법과_Spectral_Volume_기법_비교_연구.pdfDEPT_NM:기계항공공학부EMAIL:[email protected]:

Bit SLM scheme for peak to average power ratio reduction in OFDM systems

Thesis(masters) --서울대학교 대학원 :전기. 컴퓨터공학부,2008.2Maste

극초음속 유동 해석을 위한 다차원 고차 내삽 기법 개발

Thesis (doctoral)--서울대학교 대학원 :항공우주공학과,2001.Docto

전 마하수 2상 유동 해석을 위한 RoeM과 AUSMPW+ 수치기법의 확장 = Extension of RoeM and AUSMPW+ schemes for two-phase flows at all speeds

본 연구는 서울대학교 기계항공공학부 BK21사업과 국방과학연구소의 지원으로 수행되었음

Multi-dimensional Limiting Process for Three-dimensional Flow Physics Analyses

OAIID:oai:osos.snu.ac.kr:snu2005-01/104/0000004648/15SEQ:15PERF_CD:SNU2005-01EVAL_ITEM_CD:104USER_ID:0000004648ADJUST_YN:NEMP_ID:A001138DEPT_CD:446CITE_RATE:0FILENAME:3차원 유동 물리 분석을 위한 MLP기법의 개발.pdfDEPT_NM:기계항공공학부EMAIL:[email protected]:

Analysis of Oscillatory Behaviors in Shock Waves and Development of M-AUSMPW +

각 수치기법별로 충격파 주위에서 발생하는 진동현상의 원인을 분석하여 단조성을 유지하면서 충격파를 정확하게 포착할 수 있는 M-AUSMPW+를 개발하였다. 제어면과 음속천이점 위치에 대하여 FVS계열 수치기법과 AUSM계열 수치기법들이 충격파 포착시 나타내는 특성들을 분석하였고 충격파 주위의 수치진동의 원인을 찾아내었다. 음속천이점의 위치를 계산하고 이를 통해 충격파 영역에서의 물리 현상을 정확하게 반영함으로써 기존 AUSM 계열 수치기법이 가지는 충격파 주위의 물성치 진동현상을 근본적으로 제거 할 수 있었다.N