Experimental investigation on effect of partial flexibility at low aspect ratio airfoil - Part II: Installation both on suction and pressure surface

In this experimental study, flow over NACA 4412 airfoil with flexible membrane mounted both on suction surface and pressure was investigated at Reynolds number of 5x10 4 different angles attack. The smoke-wire visualization method used for to demonstrate phenomena as laminar separation bubble (LSB), leading edge tip vortices. A constant temperature anemometer (CTA) measuring the partially airfoil. Concerning visualization, experiment been conducted z/c=0.1 z/c=0.4. Besides, hot-wire by means CTA employed measure properties including values velocity, turbulence statistics Reynold stress uncontrolled controlled results showed that had several benefits compared were mainly lower size LSB, higher stall angle attack, ensuring more stable characteristics aerodynamic performance.