Mechanics & Industry
Volume 21, Number 6, 2020
|Number of page(s)||8|
|Published online||21 December 2020|
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,
K7K 7B4, Canada
* e-mail: email@example.com
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
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