Karasu, IlyasGenç, MMustafa SerdarAçikel, H. HakanAkpolat, M. Tu?rul2024-09-192024-09-192012978-162410185-4https://doi.org/10.2514/6.2012-3030https://hdl.handle.net/20.500.12483/14117American Institute for Aeronautics and Astronautics (AIAA)30th AIAA Applied Aerodynamics Conference 2012 -- 25 June 2012 through 28 June 2012 -- New Orleans, LA -- 98230Laminar separation bubble over NACA2415 aerofoil at Re=50,000 and different angles of attack was investigated in detail by performing force, pressure, hot-wire and flow visualization via smoke wire technique. From the experiments, the flow separation, the reattachment and forming the laminar separation bubble were clearly seen. From the experimental results, it was indicated that the point of separation moved towards the leading edge as the angle of attack increased. Moreover, the flow visualization results showed that as the angle of attack increased further, at the angle of attack of 13o the bubble burst and the separated flow was not able to reattach to the aerofoil surface, which indicated the stall. © 2012 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.eninfo:eu-repo/semantics/closedAccessFlow separationFlow visualizationLaminar flowReynolds numberAngles of attackHot wiresLaminar separation bubbleLow Reynolds numberSeparated flowsSmoke wire techniqueVisualization resultsAngle of attackConference Object1584159210.2514/6.2012-30302-s2.0-84880767537N/A