Figure 8
From: CNN-based flow control device modelling on aerodynamic airfoils
Comparison of the velocity and pressure fields obtained by means of CFD and CNN: (a) Gurney flap L = 1% and AoA = 0°; (b) microtab L = 1%, \(\beta \) = − 15° and AoA = 2°; (c) microtab L = 1.5%, \(\beta \) = − 45° and AoA = 6°; (d) microtab L = 2%, \(\beta \) = − 75° and AoA = 9°.
