Low-Reynolds-Number Aerodynamic Performances of the NACA 0012 and Selig–Donovan 7003 Airfoils

Abstract

A comparative study of two airfoils at low Reynolds numbers using the transitional unsteady Reynolds-averaged Navier–Stokes shear-stress transport model and the ANSYS CFX computational fluid dynamics suite is proposed. The NACA 0012 and Selig–Donovan 7003 airfoils were selected and exposed to chord-based Reynolds numbers ranging from to at angles of attack ranging from 0 to 8 deg. The adopted numerical model and setup were shown to accurately predict the main flow features. Specifically, both laminar separation without reattachment and laminar-separation-bubble flow modes were observed depending on the airfoil geometry and orientation, Reynolds number, and freestream-turbulence intensity. In general, with increasing angle of attack or Reynolds number, laminar-separation bubbles shrank and receded toward the leading edge while vortex-shedding periodicity and coherency degraded. In all cases, the Selig–Donovan 7003 proved of superior aerodynamic performance when compared to the NACA 0012, which was expected.