Airfoil/Wing Flow Control Using Flexible Extended Trailing Edge
Abstract
In this project, quasi-static and flexible trailing edge devices and fins on airfoils were studied for lift enhancement in cruising flight and drag reduction and oscillation suppression in deep stall. The aerodynamics of a NACA0012 airfoil with a static extended trailing edge was studied systematically using a combination of experimental, computational and theoretical methods. Compared with Gurney flap and conventional flap, this device enhanced lift at a smaller drag penalty, indicating a good potential to improve the cruise flight efficiency. Furthermore, drag reduction and low-frequency oscillation suppression of a NACA0012 airfoil model in deep stall were achieved by using a flexible fin attached at a suitable location on the airfoil. Detailed measurements of the velocity fields and fin kinematics revealed the significant effects of the flexible fin on the development of the flow structures in the separated flow region and the physical mechanism of the natural low-frequency oscillation. The coupled computational fluid dynamics and structural dynamics methods were developed and computations were conducted to study the corresponding problems in the experimental studies. The theoretical models were also used to provide insights into the relevant aspects of the problems. The MEMS sensors and actuators embedded on flexible elements were developed and characterized for active flow control.
Document Details
- Document Type
- Technical Report
- Publication Date
- Feb 27, 2009
- Accession Number
- ADA590187
Entities
People
- Qamar A. Shams
- Tianshu Liu
- William W. Liou
Organizations
- Western Michigan University