Flow around an airfoil with a deploying microtab device has been numerically
simulated by solving unsteady turbulent compressible two-dimensional,
Navier-Stokes equations with the OVERFLOW 2 solver. Using a Chimera/overset
grid topology, microtabs were placed at 95% of chord of a symmetric
NACA 0012 airfoil. Microtab heights on the order of 1% of chord,
deployed on the order of one (1) characteristic time unit were utilized.
The unsteady effects of tab deployment time, deployment height, and
freestream angle of attack on aerodynamic responses were also investigated.
Validation studies with experimental results for static deployed
microtabs and a dynamically deployed spoiler were also performed
to ensure accurate temporal and spatial resolution of the numerical
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