Abstract
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.
Full Text 
Sign-in/Register to access full text options
Sign-in/Register to access full text options 
Published version (
Free)
Free) 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callMore From: ARCHIVE: Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 1989-1996 (vols 203-210)
Paper Title
Journal
Date
