Flow past a swept wing

9 different values of the angle of attack from 0° to 8° were tested in a total time of 150 seconds

Pressure for angle of attack 3 degrees

Pressure distribution on the wing section A for angles of attack 3° and 7°

Variation of the lift coefficient with respect to the angle of attack

Flow past an aircraft

Two different values of the yaw angle were tested in a total time of 250 seconds

Velocity Magnitude contours for yaw angle 0°

Pressure distribution on a section of the vertical stabilizer for yaw angle 0° and 3°