Abstract: This work explores the control of boundary layer separation that occurs over an airfoil at high angles at attack, causing stall. For this study, a NACA 0008 thin, symmetric, airfoil section has been selected due to its well-documented and easily verified performance characteristics. The airfoil was equipped with a plasma actuator, and force measurements were taken using a sting balance to determine the change in lift force. The airfoil was operated at a free stream speed of 20 m/s for a chord Reynolds number of . The plasma actuator used in this experiment in theory produces a spanwise array of streamwise vortices. It consists of two copper electrodes separated by a dielectric, and was operated at a peak-topeak voltage of 14kV. It was found that while there was no major effect on the stall condition, the actuator has shown that it can increase the lift coefficient by an average of 5%, and up to 10%.
Publication Year: 2009
Publication Date: 2009-06-14
Language: en
Type: article
Indexed In: ['crossref']
Access and Citation
AI Researcher Chatbot
Get quick answers to your questions about the article from our AI researcher chatbot