An LES Investigation of the Separated Flow Past An Airfoil at High Angle of Attack
Publication date
2001
Document type
Conference paper
Author
Jovicic, Nikola
Organisational unit
Conference
4th Workshop on Direct and Large Eddy Simulation, Enschede, The Netherlands, July 18–20, 2001
Publisher
Kluwer Academic Publishers
Series or journal
ERCOFTAC Series
Periodical volume
8
Book title
Direct and Large-Eddy Simulation IV
First page
165
Last page
172
Peer-reviewed
✅
Part of the university bibliography
Nein
Language
English
Abstract
An investigation of the separated flow past an unswept wing (NACA-4415 airfoil) at high angle of attack ($\alpha$ = 18{\textdegree}) was carried out based on large-eddy simulations. As a first step a relatively low chord Reynolds number of Rec= 20, 000 was chosen yielding a leading-edge stall. The flow field in this range of $\alpha$ and Recis dominated by asymmetric vortex shedding with a Strouhal number St{\textasciiacutex} ≈ 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.
Cite as
Breuer, M., Jovičić, N. (2001). An LES Investigation of the Separated Flow Past an Airfoil at High Angle of Attack. In: Geurts, B.J., Friedrich, R., Métais, O. (eds) Direct and Large-Eddy Simulation IV. ERCOFTAC Series, vol 8. Springer, Dordrecht. https://doi.org/10.1007/978-94-017-1263-7_20
Version
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