Active Flow Control–High-Lift Wing with Microject Implementation
Visualization showing microjet implementation close to the flap trailing edge of the high-lift Common Research Model wing. Microjet implementation generates two counter-rotating vortices at the flap trailing edge. These vortices change the airfoil’s effective camber and chord to increase lift. Contour color indicates Mach number at a cross section of the wing during landing maneuvers.
Image Credit: NASA/Ames, Sheida Hosseini