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
- 학술대회자료
- 저자정보
- 발행연도
- 2014.4
- 수록면
- 105 - 116 (12page)
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초록· 키워드
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Effect of flow actuation driven by low current DC surface glow discharge plasma actuator is studied numerically 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
ABSTRACT
1. Introduction
2. Numerical Modelling
3. Validation
4. Results and discussions
5. Summary
REFERENCES
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UCI(KEPA) : I410-ECN-0101-2016-558-000990330