Flow past a cylinder and over a flat wall

Velocity magnitude contours on the cylinder and on the wall

Velocity magnitude isolines on the cylinder and on the wall

Velocity distribution on the cylinder

Velocity distribution on the flat wall

Flow past a swept wing

Pressure distribution at the spanwise section A (AoA = 3 deg)

Flow past an aircraft (wing – body – nacelle)

Pressure distribution on a wing section ( y / b = 0.5 )

Flow past a high-lift wing

Views close to the flap and the slat

Pressure distribution at the spanwise section A (AoA = 3 deg)