Particle image velocimetry investigation of an aerofoil with a Gurney flap

摘要

The current paper reviews the research on NACA 23012 and FX66-17AII-182 aerofoils, aerodynamic performance for different angles of attack at Reynolds number Re ≈ 3 × 105, based on chord, both with clean configuration and the flaps. Flow field around the aerofoil was measured using a two-dimensional particle image velocimetry (PIV) system, and the measurement of static pressure on aerofoil surface was carried out. The current article also describes new methods in Gurney flap research, using the two-dimensional PIV system and Kutta–Joukowski lift theorem or static pressure assumption to evaluate aerofoil lift.