지원사업
학술연구/단체지원/교육 등 연구자 활동을 지속하도록 DBpia가 지원하고 있어요.
커뮤니티
연구자들이 자신의 연구와 전문성을 널리 알리고, 새로운 협력의 기회를 만들 수 있는 네트워킹 공간이에요.
논문 기본 정보
- 자료유형
- 학위논문
- 저자정보
- 지도교수
- Shin Jichul
- 발행연도
- 2015
- 저작권
- 울산대학교 논문은 저작권에 의해 보호받습니다.
이용수3
이 논문의 연구 히스토리 (2)
- 이 논문의 후속연구가 궁금하신가요?
- 연관 학술논문 또는 학술발표를 통해 보다 발전된 연구결과를 확인하실 수 있습니다.
- 이 논문의 연구 히스토리 확인하기
초록· 키워드
오류제보하기
Effect of flow actuation driven by low current DC surface glow discharge plasma actuator is studied numerically by using OPENFOAM. Numerical model of the source of flow actuation is obtained by physical modeling of ion pressure rise created in DC plasma sheath near the cathode.
Modeled plasma flow actuator is tested with NACA0012 airfoil in order to demonstrate the actuation effect in low speed flows. Dynamic situation of the airfoil is obtained by rotating the airfoil within a certain range of angle of attack at a specific rotating speed. In order to simulate the motion of oscillating airfoil, computational domain is split into two parts; far field and near the airfoil. Sliding mesh is applied to a circular domain near the airfoil. To simulate unsteady plasma actuator, plasma actuator is added in Navier Stocke’s equation in term of body force. Simulated plasma actuator is placed on the upper surface of the airfoil at different positions. As the angle of attack changes, flow around the airfoil produces various drag and lift force and dynamic stall may happen. By changing actuation authority according to the change in angle of attach, stabilization of unsteady flow field is achieved and hence constant aerodynamic performance is maintained. The relevant relationship between frequency of plasma actuator and reduced frequency is investigated.
Modeled plasma flow actuator is tested with NACA0012 airfoil in order to demonstrate the actuation effect in low speed flows. Dynamic situation of the airfoil is obtained by rotating the airfoil within a certain range of angle of attack at a specific rotating speed. In order to simulate the motion of oscillating airfoil, computational domain is split into two parts; far field and near the airfoil. Sliding mesh is applied to a circular domain near the airfoil. To simulate unsteady plasma actuator, plasma actuator is added in Navier Stocke’s equation in term of body force. Simulated plasma actuator is placed on the upper surface of the airfoil at different positions. As the angle of attack changes, flow around the airfoil produces various drag and lift force and dynamic stall may happen. By changing actuation authority according to the change in angle of attach, stabilization of unsteady flow field is achieved and hence constant aerodynamic performance is maintained. The relevant relationship between frequency of plasma actuator and reduced frequency is investigated.
목차
CONTENTSAcknowledgements vABSTRACT 1Chapter 1 41.1. Dynamic stall phenomenon 41.2. Flow control 71.2.1 Active flow separation control techniques 8Moving objects/surface actuator 111.2.2 Passive flow separation control techniques 121.3. Flow control by plasma actuator 131.4. Review of related research 151.5. Constitution of the thesis 17Chapter 2 172.1. Theory 172.1.1. Governing equations 172.1.2. RANS method 182.1.3. Turbulence modelling 192.1.4. Dynamics 202.2. Method 212.2.1. Design space 212.2.2. Meshing 242.2.3. Boundary conditions 262.2.4. Numerical schemes and numerical solver 27Chapter 3 293.1. Flow over a static airfoil 293.1.1. Introduction 293.1.2. Numeric and results 293.1.3. Conclusions 303.2. Flow over an oscillating airfoil 313.2.1. Introduction 313.2.2. Numeric and results 313.2.3. Conclusions 33Chapter 4 344.1. Introduction 344.2. Results and discussion 354.3 . Conclusions 42References 43
최근 본 자료
댓글(0)
0