Abstract
An investigation of the separated flow past an unswept wing (NACA-4415 airfoil) at high angle of attack (α = 18°) was carried out based on large-eddy simulations. As a first step a relatively low chord Reynolds number of Re c = 20, 000 was chosen yielding a leading-edge stall. The flow field in this range of α and Re c is dominated by asymmetric vortex shedding with a Strouhal number St′ ≈ 0.2. A strong vortex develops almost periodically in the vicinity of the trailing edge. The life cycle of this vortex structure is controlling the flow field. At the leeward side of the airfoil a large clockwise rotating recirculation region of nearly constant pressure exists. A periodically occurring shedding motion of this vortical structure into the wake is not observed. The entire flow field is very similar to the previously investigated flow past an inclined flat plate.KeywordsLarge-eddy simulationseparated flowairfoilhigh angle of attack
Sign-in/Register to access full text options 
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 callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
