Issue |
Mechanics & Industry
Volume 21, Number 6, 2020
|
|
---|---|---|
Article Number | 620 | |
Number of page(s) | 8 | |
DOI | https://doi.org/10.1051/meca/2020094 | |
Published online | 21 December 2020 |
Regular Article
Mode and regime identification for a static NACA0012 airfoil at transitional Reynolds numbers
Department of Mechanical and Aerospace Engineering Royal Military College of Canada Kingston,
Ontario
K7K 7B4, Canada
* e-mail: benaissa-a@rmc.ca
Received:
21
February
2020
Accepted:
25
November
2020
This work examines the flow structure modes in the boundary layer and in the wake of a NACA0012 airfoil in static conditions at transitional chord-based Reynolds numbers (Rec), for small angles of attack (α). A laminar mode, with a laminar separation of the boundary layer and laminar Kármán streets in the wake, was first observed for Rec < 61400 and α = 0°. For 77 000 < Rec < 118600, which corresponds to a regime between laminar and transitional mode called subcritical mode, the boundary layer exhibited a long separation bubble reattached close to the trailing edge, and the wake showed a turbulent Kármán street. Finally, for higher Rec and α, a critical transition mode consisted of a long bubble followed by a turbulent separation, and a less structured vortex street in the wake of the airfoil.
Key words: Laminar separation / transitional Reynolds Number / Wake of a NACA0012 airfoil
© AFM, EDP Sciences 2020
Current usage metrics show cumulative count of Article Views (full-text article views including HTML views, PDF and ePub downloads, according to the available data) and Abstracts Views on Vision4Press platform.
Data correspond to usage on the plateform after 2015. The current usage metrics is available 48-96 hours after online publication and is updated daily on week days.
Initial download of the metrics may take a while.